The present invention relates to a variable geometry turbine assembly. The present invention relates to a variable geometry turbine assembly of a variable geometry turbomachine and particularly, but not exclusively, of a variable geometry turbocharger. The present invention also relates to an actuation mechanism for moving a movable wall member of a variable geometry turbine. Turbochargers are well known devices for supplying air to the intake of an internal combustion engine at pressures above atmospheric pressure (boost pressures). A conventional turbocharger essentially comprises an exhaust gas driven turbine wheel mounted on a rotatable shaft within a turbine housing connected downstream of an engine outlet manifold. Rotation of the turbine wheel rotates a compressor wheel mounted on the other end of the shaft within a compressor housing. The compressor wheel delivers compressed air to the engine intake manifold. The turbocharger shaft is conventionally supported by journal and thrust bearings, including appropriate lubricating systems, located within a central bearing housing connected between the turbine and compressor wheel housings.

In known turbochargers, the turbine stage comprises a turbine chamber within which the turbine wheel is mounted; an annular inlet passageway defined between facing radial walls arranged around the turbine chamber; an inlet arranged around the inlet passageway; and an outlet passageway extending from the turbine chamber. The passageways and chambers communicate such that pressurised exhaust gas admitted to the inlet chamber flows through the inlet passageway to the outlet passageway via the turbine and rotates the turbine wheel. It is also known to improve turbine performance by providing vanes, referred to as nozzle vanes, in the inlet passageway so as to deflect gas flowing through the inlet passageway towards the direction of rotation of the turbine wheel.

Turbines may be of a fixed or variable geometry type. Variable geometry turbines differ from fixed geometry turbines in that the size of the inlet passageway can be varied to optimise gas flow velocities over a range of mass flow rates so that the power output of the turbine can be varied to suite varying engine demands. For instance, when the volume of exhaust gas being delivered to the turbine is relatively low, the velocity of the gas reaching the turbine wheel is maintained at a level which ensures efficient turbine operation by reducing the size of the annular inlet passageway. Turbochargers provided with a variable geometry turbine are referred to as variable geometry turbochargers.

In one known type of variable geometry turbine an axially moveable wall member, generally referred to as a "nozzle ring" defines one wall of the inlet passageway. The position of the nozzle ring relative to a facing wall of the inlet passageway is adjustable to control the axial width of the inlet passageway. Thus, for example, as gas flow through the turbine decreases, the inlet passageway width may be decreased to maintain gas velocity and optimise turbine output. The nozzle ring is provided with vanes which extend into the inlet and through slots provided in a "shroud" defining the facing wall of the inlet passageway to accommodate movement of the nozzle ring. The vanes are at a fixed angle relative to the radius of the nozzle ring. A variable geometry turbocharger including such a variable geometry turbine is for instance disclosed in US 5,868,552.

In different arrangements the nozzle ring is fixed and the shroud is axially moveable so as to control the axial width of the inlet passageway.

In current variable geometry turbochargers the moveable wall member (i.e. the nozzle ring or the shroud) is mounted on the end of push rods that are attached, at their other end, to a rotating yoke pivoting in an arc about a cross shaft. The yoke is arranged such that its rotation moves the push rods in the axial direction, so as to move the moveable wall member in the axial direction.

The yoke and push rods are mounted internally to the bearing housing. In this case, seals are required where the push rods pass through the bearing housing wall into the turbine housing. These seals are relatively expensive and require water cooling, which increases the complexity and cost of the variable geometry to the charger.

In an alternative arrangement, the push rods and the yoke are mounted in a cavity in the turbine housing. This arrangement does not require the seals of the bearing housing mounted arrangement. However, this arrangement is large and bulky in nature to allow for the mounting of the moveable wall member, push rods, and yoke. This results in a large overall turbine housing, which also increases its thermal inertia. Furthermore, due to the large cavities required to house all of the moving components, an increased pressure differential is experienced during filling and scavenging of the exhaust gas in the housing.

It is one object of the present invention to obviate or mitigate the aforesaid disadvantages. It is also an object of the present invention to provide for an improved or alternative variable geometry turbine assembly. It is also an object of the present invention to provide for an improved or alternative actuation mechanism for a movable wall member of a variable geometry turbine assembly.

According to a first aspect of the invention there is provided a variable geometry turbine assembly comprising: a turbine wheel mounted within a turbine housing for rotation about a turbine axis; an annular inlet passageway extending radially inwards towards the turbine wheel; the annular inlet passageway being defined between a surface of a movable wall member and a facing wall; the movable wall member being movable in the axial direction so as to vary the size of the annular inlet passageway, and an actuation mechanism arranged to move the movable wall member axially relative to the facing wall; the actuation mechanism comprising: a carrier member, the carrier member being movable in the axial direction and coupled to the movable wall member such that as the carrier member is moved in the axial direction, the moveable wall member is moved in the axial direction a cam member provided with at least one formation; the carrier member being coupled to at least one co-operating formation such that as the at least one co-operating formation is moved in the axial direction, the carrier member is moved in the axial direction, wherein one of the at least one formation and the at least one co-operating formation is a radially extending formation and the other defines a complimentary recess for receiving the radially extending formation, the at least one formation or the at least one co-operating formation extending in both the circumferential direction and the axial direction; the actuation mechanism is arranged such that as the cam member is rotated relative to the carrier member, the at least one formation and the at least one cooperating formation engage such that the at least one co-operating formation is moved in the axial direction, thereby moving the carrier member in the axial direction, and thereby moving the movable wall member in the axial direction so as to vary the size of the inlet passageway; the turbine assembly further comprising a nozzle ring having a plurality of circumferentially distributed inlet vanes and an annular shroud provided with a plurality of slots for receiving the inlet vanes of the nozzle ring as the shroud is moved axially relative to the nozzle ring; wherein the shroud comprises the movable wall member; and the nozzle ring and shroud are mounted on the same axial side of the inlet passageway.

This is advantageous in that it provides a relatively compact variable geometry turbine arrangement. In addition, the cam member, carrier member and movable wall member can be formed as a self-contained cartridge that is relatively compact and easy to install.

Furthermore, the above arrangement does not require axial push rods to move the moveable wall member and so does not require the sealing arrangement necessary where push rods are used, which is relatively expensive, wears easily and requires water cooling. Therefore the above arrangement is relatively inexpensive, durable and compact. It will be appreciated that where something is referred to as "radially extending" or "extending in the radial direction", this refers to extending generally in the radial direction (the radial direction relative to the turbine axis) and, unless otherwise stated, is not to be interpreted as specifically requiring that it extends substantially parallel to the radial direction.

Similarly, where something is referred to as "axially extending" or "extending in the axial direction" this refers to extending generally in the axial direction (the direction of the turbine axis) and, unless otherwise stated, is not to be interpreted as specifically requiring that it extends substantially parallel to the axial direction.

Optionally the nozzle ring comprises an annular radially extending wall, the plurality of circumferentially distributed inlet vanes extend axially inboard from an inboard surface of the radially extending wall and the annular shroud comprises an annular radially extending wall provided with said plurality of slots, wherein the radially extending wall of the nozzle ring is mounted axially outboard of the radial wall of the shroud.

Optionally the variable geometry turbine assembly comprises a bearing housing arranged to house at least one bearing that rotatably supports a shaft on which the turbine wheel is mounted and the shroud and the nozzle ring are mounted on the same axial side of the inlet passageway as the bearing housing.

Alternatively, the shroud and nozzle ring may be mounted on an opposite axial side of the inlet passageway to the bearing housing. In this regard, the shroud and nozzle ring may be mounted on the same axial side of the inlet passageway as the turbine housing.

Optionally the nozzle ring is substantially fixed in the axial direction. In this regard, the inlet vanes of the nozzle ring are disposed in the inlet passageway. The inlet vanes may extend substantially across the width of the inlet passageway. Optionally the nozzle ring is also movable in the axial direction, so as to vary the axial extent of the inlet vanes in the inlet passageway.

Optionally the carrier member is annular. Optionally the carrier member extends in the circumferential direction about the turbine axis.

Optionally the cam member and the carrier member axially overlap for at least one axial position of the movable wall member. Optionally the cam member is disposed radially outwardly of the movable wall member. Alternatively, the cam member may be disposed radially inwardly of the movable wall member.

Optionally the at least one formation and the at least one co-operating formation extend in both the circumferential direction and the axial direction. Preferably only the at least one formation or the at least one co-operating formation extends in both the circumferential direction and the axial direction.

According to a second aspect of the invention there is provided a variable geometry turbine assembly comprising: a turbine wheel mounted within a turbine housing for rotation about a turbine axis; an annular inlet passageway extending radially inwards towards the turbine wheel; the annular inlet passageway being defined between a surface of a movable wall member and a facing wall; the movable wall member being movable in the axial direction so as to vary the size of the annular inlet passageway, and an actuation mechanism arranged to move the movable wall member axially relative to the facing wall; the actuation mechanism comprising: an annular carrier member, the carrier member being movable in the axial direction and coupled to the movable wall member such that as the carrier member is moved in the axial direction, the moveable wall member is moved in the axial direction a cam member mounted for rotation about the turbine axis; the cam member is provided with at least one formation; the carrier member being coupled to at least one co-operating formation such that as the at least one co-operating formation is moved in the axial direction, the carrier member is moved in the axial direction, wherein one of the at least one formation and the at least one co-operating formation is a radially extending formation and the other defines a complimentary recess to receive the radially extending formation, the at least one formation extending in both the circumferential direction and the axial direction; the actuation mechanism is arranged such that as the cam member is rotated, the at least one formation and the at least one co-operating formation engage such that the at least one co-operating formation is moved in the axial direction, thereby moving the carrier member in the axial direction, and thereby moving the movable wall member in the axial direction so as to vary the size of the inlet passageway; wherein the cam member and the carrier member axially overlap for at least one axial position of the movable wall member.

This is advantageous in that it provides a relatively compact variable geometry turbine arrangement. In addition, the cam member, carrier member and movable wall member can be formed as a self-contained cartridge that is relatively compact and easy to install. Furthermore, the above arrangement does not require axial push rods to move the moveable wall member and so does not require the sealing arrangement necessary where push rods are used, which is relatively expensive, wears easily and requires water cooling. Therefore the above arrangement is relatively inexpensive, durable and compact.

Optionally the carrier member is annular. Optionally the carrier member extends in the circumferential direction about the turbine axis. Optionally the carrier member comprises an annular wall that extends in the circumferential direction about the turbine axis.

Optionally the cam member and the carrier member axially overlap for a plurality of axial positions of the movable wall member. Optionally the turbine assembly further comprises a nozzle ring having a plurality of circumferentially distributed inlet vanes and an annular shroud provided with a plurality of slots for receiving the inlet vanes of the nozzle ring as the shroud is moved axially relative to the nozzle ring. The nozzle ring and shroud may be mounted on the same or different sides of the inlet passageway. Where the shroud comprises the movable wall member, the nozzle ring and shroud may be mounted on the same axial side of the inlet passageway.

Optionally the cam member is disposed radially outwardly of the movable wall member. Alternatively, the cam member may be disposed radially inwardly of the movable wall member.

According to a third aspect of the invention there is provided there is provided a variable geometry turbine assembly comprising: a turbine wheel mounted within a turbine housing for rotation about a turbine axis; an annular inlet passageway extending radially inwards towards the turbine wheel; the annular inlet passageway being defined between a surface of a movable wall member and a facing wall; the movable wall member being movable in the axial direction so as to vary the size of the annular inlet passageway, and an actuation mechanism arranged to move the movable wall member axially relative to the facing wall; the actuation mechanism comprising: a carrier member, the carrier member being movable in the axial direction and coupled to the movable wall member such that as the carrier member is moved in the axial direction, the moveable wall member is moved in the axial direction a cam member provided with at least one formation; the carrier member being coupled to at least one co-operating formation such that as the at least one co-operating formation is moved in the axial direction, the carrier member is moved in the axial direction, wherein one of the at least one formation and the at least one co-operating formation is a radially extending formation and the other defines a complimentary recess for receiving the radially extending formation, the at least one formation or the at least one co-operating formation extending in both the circumferential direction and the axial direction; the actuation mechanism is arranged such that as the cam member is rotated relative to the carrier member, the at least one formation and the at least one cooperating formation engage such that the at least one co-operating formation is moved in the axial direction, thereby moving the carrier member in the axial direction, and thereby moving the movable wall member in the axial direction so as to vary the size of the inlet passageway; wherein the cam member is disposed radially outwardly of the movable wall member. This is advantageous in that it provides a relatively compact variable geometry turbine arrangement. In addition, the cam member, carrier member and movable wall member can be formed as a self-contained cartridge that is relatively compact and easy to install.

Furthermore, the above arrangement does not require axial push rods to move the moveable wall member and so does not require the sealing arrangement necessary where push rods are used, which is relatively expensive, wears easily and requires water cooling. Therefore the above arrangement is relatively inexpensive, durable and compact.

Optionally the cam member is annular. Optionally the cam member extends in the circumferential direction about the turbine axis.

Optionally the movable wall member is annular. Optionally the movable wall member extends in the circumferential direction about the turbine axis.

Optionally the turbine assembly further comprises a nozzle ring having a plurality of circumferentially distributed inlet vanes and an annular shroud provided with a plurality of slots for receiving the inlet vanes of the nozzle ring as the shroud is moved axially relative to the nozzle ring.

The nozzle ring and/or the shroud may comprise the movable wall member.

The nozzle ring and shroud may be mounted on the same or different sides of the inlet passageway. Where the shroud comprises the movable wall member, the nozzle ring and shroud may be mounted on the same axial side of the inlet passageway. Optionally the carrier member is annular.

Optionally the cam member and the carrier member axially overlap for at least one axial position of the movable wall member. Optionally the at least one formation and the at least one co-operating formation extend in both the circumferential direction and the axial direction. Preferably only the at least one formation or the at least one co-operating formation extends in both the circumferential direction and the axial direction.

Any of the first to the third aspects of the invention may comprise any of the following features, in any combination.

The movable wall member may be part of the shroud. In this case, the carrier member may be coupled to the shroud such that as the carrier member moves axially, the shroud moves axially. The carrier member may be part of the shroud such that as the carrier member moves axially, the shroud moves axially.

In this case, the shroud and nozzle ring may be mounted on the same axial side of the inlet passageway. The nozzle ring may be substantially fixed in the axial direction.

The movable wall member may be part of the nozzle ring. In this case, the carrier member may be coupled to the nozzle ring such that as the carrier member moves axially, the nozzle ring moves axially. The carrier member may be part of the nozzle ring such that as the carrier member moves axially, the nozzle ring moves axially.

In this case, the shroud and nozzle ring may be mounted on opposite axial sides of the inlet passageway. The shroud may be substantially fixed in the axial direction. Optionally the nozzle ring comprises an annular radially extending wall, the plurality of circumferentially distributed inlet vanes extend axially inboard from an inboard surface of the radially extending wall and the annular shroud comprises an annular radially extending wall provided with said plurality of slots, wherein the radially extending wall of the nozzle ring is mounted axially outboard of the radial wall of the shroud.

Optionally the variable geometry turbine assembly comprises a bearing housing arranged to house at least one bearing that rotatably supports a shaft on which the turbine wheel is mounted and the shroud and the nozzle ring are mounted on the same axial side of the inlet passageway as the bearing housing. Alternatively, the shroud and nozzle ring may be mounted on an opposite axial side of the inlet passageway to the bearing housing. In this regard, the shroud and nozzle ring may be mounted on the same axial side of the inlet passageway as the turbine housing.

Optionally the nozzle ring is substantially fixed in the axial direction. In this regard, the inlet vanes of the nozzle ring are disposed in the inlet passageway. The inlet vanes may extend substantially across the width of the inlet passageway. Optionally the nozzle ring is also movable in the axial direction, so as to vary the axial extent of the inlet vanes in the inlet passageway.

Optionally the one of the at least one formation and the at least one co-operating formation that extends in both the circumferential direction and the axial direction is said complimentary recess and the other is said radially extending formation.

Optionally the at least one co-operating formation is said radially extending formation and the at least one formation defines said complimentary recess to receive the radially extending formation.

Optionally the at least one formation is said complimentary recess and extends in both the circumferential direction and the axial direction and the at least one co-operating formation is said radially extending formation. Optionally the co-operating formation is part of the carrier member.

Alternatively, the at least one co-operating formation may be a separate entity to the carrier member. In this case, optionally the at least one co-operating formation is a radially extending coupling element. Optionally the carrier member has an annular wall provided with at least one radially extending bore and the at least one radially extending coupling element is received in the at least one radially extending bore such that as the at least one coupling element is moved in the axial direction, the carrier member is moved in the axial direction. The at least one coupling element may be elongate, having a longitudinal axis that is substantially parallel to the radial direction. The longitudinal axis of the at least one coupling element may be substantially straight. The at least one coupling element may be a pin. The at least one coupling element may be substantially cylindrical.

Optionally the one of the at least one formation and the at least one co-operating formation that extends in both the circumferential direction and the axial direction defines at least part of a helix. Optionally the one of the at least one formation and the at least one co-operating formation that extends in both the circumferential direction and the axial direction is substantially helical.

Optionally the complimentary recess is a radially extending slot.

The carrier member may be substantially rotationally fixed about the turbine axis.

Optionally the at least one formation is said complimentary recess and extends in both the circumferential direction and the axial direction and the at least one co-operating formation is said radially extending formation and a wall member is provided with at least one axially extending slot, the at least one co-operating formation being received in the at least one axially extending slot and wherein the actuation mechanism is arranged such that as the cam member is rotated relative to the carrier member, the at least one formation and the at least one co-operating formation engage such that the at least one co-operating formation is moved in the axial direction, along the at least one axially extending slot in said wall member, thereby moving the carrier member in the axial direction and thereby moving the movable wall member in the axial direction, so as to vary the width of the inlet passageway. Optionally, where the shroud comprises the movable wall member, the nozzle ring and shroud are arranged such that as the shroud is moved axially, the engagement of the vanes with the slots guides the shroud in the axial direction. Optionally the engagement of the vanes with the slots limits the rotation of the shroud about the turbine axis, as the shroud is moved in the axial direction. Optionally the engagement of the vanes with the slots substantially prevents the shroud from rotating about the turbine axis, as the shroud is moved in the axial direction. Optionally the nozzle ring is substantially rotationally fixed about the turbine axis.

Optionally the nozzle ring and shroud are arranged such that as the shroud is moved axially, the engagement of the at least one formation and the at least one co-operating formation rotates the shroud such that, for each slot in the shroud, at least a portion of an inner surface that defines the slot abuts against an opposed surface of a vane of the nozzle ring that is received within the slot. This advantageously reduces leakage of exhaust gas from the inlet passageway, through the slots in the shroud.

Optionally the nozzle ring and shroud are arranged such that as the cam member is rotated in a first rotational direction, for each slot in the shroud, a first portion of an inner surface that defines the slot abuts against an opposed surface of a vane of the nozzle ring that is received within the slot and as the cam member is rotated in a second rotational direction, for each slot in the shroud, a second portion of an inner surface that defines the slot abuts against an opposed surface of a vane of the nozzle ring that is received within the slot. It will be appreciated that the first and second rotational directions are opposite to each other. Optionally the variable geometry turbine assembly comprises a bearing housing arranged to house at least one bearing that rotatably supports a shaft on which the turbine wheel is mounted and the shroud and the actuation mechanism is mounted on the same axial side of the inlet passageway as the bearing housing. Optionally where the at least one formation defines said complimentary recess, the recess is provided in a circumferential section of the cam ring that is of greater radial thickness than the remainder of the cam ring.

Optionally where the at least one formation defines said complimentary recess and the at least one co-operating formation is said radially extending formation and is part of the carrier member, the complimentary recess has an open end for receipt of the cooperating formation.

Optionally the cam member is provided with a plurality of said formations, distributed in the circumferential direction. Optionally the carrier member is coupled to a plurality of said co-operating formations, distributed in the circumferential direction. Optionally where the shroud comprises the movable wall member, the shroud also comprises the carrier member. Alternatively, the carrier member may be a separate entity to the shroud.

The nozzle ring may comprise the movable wall member. In this case, the nozzle ring may comprise the carrier member.

Optionally at least one seal is provided between the movable wall member and an adjacent surface such so as to substantially prevent exhaust gas from the inlet passageway passing outboard of the seal.

The seal may be mounted to the movable wall member, to move axially with the movable wall member. Alternatively, the seal may be axially fixed relative to said adjacent surface. Where the shroud comprises said movable wall member, the shroud may be slidably mounted in the nozzle ring, with the at least one seal provided between a surface of the shroud and an opposed surface of the nozzle ring. The at least one seal may be provided between an annular axially extending flange of the seal, that extends inboard from a radial wall of the shroud that forms the movable wall member and an opposed surface of the nozzle ring.

Alternatively, or additionally, optionally said annular axially extending flange forms a radially inner flange, wherein the shroud comprises a radially outer annular axially extending flange that extends inboard from a radial wall of the shroud, wherein the at least one seal is provided between the radially outer flange and an opposed surface of the nozzle ring.

The nozzle ring may comprise a heat shield integrally formed with the nozzle ring and disposed between the turbine wheel and a component of the variable geometry turbine assembly, arranged to protect said component from the hot gases in the turbine. The heat shield may be formed by a radially inner section of the nozzle ring, disposed between the turbine wheel and said component of the variable geometry turbine assembly.

The heat shield section may be made of a heat resistant material, including stainless steel (e.g. 304 or pl33), Inconel or any suitable heat resistant material.

The variable geometry turbine assembly may comprise a biasing member arranged to bias the tips of the guide vanes into contact with the facing wall. The biasing member may be a resiliently deformable annular member.

Optionally the heat shield is not attached to the nozzle ring and the biasing member is arranged to bias the tips of the guide vanes into contact with the facing wall without exerting an inboard axial force on the heat shield. In this regard, the heat shield may comprise an annular lip that is disposed outboard of the biasing member.

Preferably the actuation mechanism is arranged such that as the cam member is rotated relative to the carrier member in first and second rotational directions, the carrier member, and so the movable wall member, is moved in the first and second axial directions respectively.

Preferably the second axial direction is opposite to the first axial direction.

Preferably the second rotational direction is opposite to the first rotational direction.

The variable geometry turbine assembly may further comprise a support member comprising an annular wall, wherein the carrier member is axially slidably mounted on a radially outer surface of the annular wall of the support member. The carrier member may be mounted directly on the support member.

Preferred embodiments of the variable geometry turbine assembly of the first to the third aspects of the invention are the first to the fourth embodiments of the invention shown in Figures 1 to 95. The variable geometry turbine assembly of the first to the third aspects of the invention may have any of the features of the first to the fourth embodiments. A wall member of the variably geometry turbine assembly may be provided with a formation that is arranged to engage with a complimentary formation on the nozzle ring, the carrier member, the cam member and/or the support member such that when the formations are engaged, the nozzle ring, carrier member, cam member and/or the support member is in a specific rotational orientation about the turbine axis.

The formation and complimentary formation may be a recess or protrusion, or vice versa. The wall member may be a wall member of a bearing housing.

The support member may be provided with the complimentary formation, such that when the formations are engaged, the support member is in a specific rotational orientation about the turbine axis, relative to the bearing housing. The support member may be provide with a second formation for engagement with a second complimentary formation on the nozzle ring or shroud such that when the second formation and second complimentary formation are engaged the nozzle ring or shroud, respectively, is in a specific rotational orientation about the turbine axis, relative to the support member. The second formation and second complimentary formation may be a recess or protrusion, or vice versa.

According to a fourth aspect of the invention there is provided a variable geometry turbine assembly comprising: a turbine wheel mounted within a turbine housing for rotation about a turbine axis; an annular inlet passageway extending radially inwards towards the turbine wheel; the annular inlet passageway being defined between a surface of a movable wall member and a facing wall of the variable geometry turbine assembly; the movable wall member being movable in the axial direction so as to vary the size of the annular inlet passageway, and an actuation mechanism arranged to move the movable wall member axially relative to the facing wall; the actuation mechanism comprising: a carrier member, the carrier member being movable in the axial direction and coupled to the movable wall member such that as the carrier member is moved in the axial direction, the moveable wall member is moved in the axial direction, the carrier member having an annular wall provided with at least one radially extending bore; at least one radially extending coupling element received in the at least one radially extending bore in the annular wall of the carrier member such that as the at least one coupling element is moved in the axial direction, the carrier member is moved in the axial direction; a cam member mounted for rotation about the turbine axis, the cam member having an annular wall provided with at least one slot defined by at least one surface of the annular wall, the at least one slot extending in both the circumferential direction and the axial direction; the at least one coupling element also being received in the at least one slot in the cam member; wherein a wall member is provided with at least one axially extending slot, the at least one coupling element also being received in at least one axially extending slot; and wherein the actuation mechanism is arranged such that as the cam member is rotated about the turbine axis, the at least one slot in the annular wall of the cam member is moved relative to the at least one coupling element, with the at least one surface of the cam member that defines the at least one slot acting on the at least one coupling element to move the at least one coupling element in a the axial direction, along the at least one axially extending slot in said wall member, thereby moving the carrier member in the axial direction and thereby moving the movable wall member in the axial direction, so as to vary the width of the inlet passageway.

This is advantageous in that it provides a relatively compact variable geometry turbine arrangement. In addition, the cam member, carrier member and movable wall member can be formed as a self-contained cartridge that is relatively compact and easy to install.

Furthermore, the above arrangement does not require axial push rods to move the moveable wall member and so does not require the sealing arrangement necessary where push rods are used, which is relatively expensive, wears easily and requires water cooling. Therefore the above arrangement is relatively inexpensive, durable and compact.

The facing wall may be a facing wall of the housing. Preferably the actuation mechanism is arranged such that as the cam member is rotated about the turbine axis in first and second rotational directions, the at least one slot in the cam member is moved relative to the at least one coupling element, with the at least one surface of the cam member that defines the at least one slot acting on the at least one coupling element to move the at least one coupling element in first and second axial directions respectively, along the at least one axially extending slot in said wall member, thereby moving the carrier member in the first and second axial directions respectively and thereby moving the movable wall member in the first and second axial directions respectively. Preferably the second axial direction is opposite to the first axial direction.

Preferably the second rotational direction is opposite to the first rotational direction.

The carrier member may be axially fixed relative to the movable wall member. The carrier member may be rotationally fixed relative to the movable wall member. The carrier member may be fixed directly to the movable wall member. The carrier member may be arranged such that it is rotationally fixed about the turbine axis. In this regard, preferably as the carrier member moves axially, it does not rotate about the turbine axis.

The at least one radially extending bore in the annular wall of the carrier member may extend along a longitudinal axis that is substantially parallel to the radial direction. The longitudinal axis of the at least one radially extending bore may be substantially straight.

The at least one coupling element may be axially fixed relative to the carrier member.

The at least one radially extending bore in the annular wall of the carrier member and the at least one coupling element may be arranged such that as the at least one coupling element is moved in the first and second axial directions, the carrier member is moved in the first and second axial directions respectively.

The at least one radially extending bore may have an axial extent that is substantially the same as, or slightly greater than, the axial extent of the at least one coupling element such that as the at least one coupling element is moved in the first and second axial directions, the carrier member is moved in the first and second axial directions respectively.

The annular wall of the carrier member may have a radially inner and/or outer surface that extends substantially parallel to the axial direction.

The annular wall of the carrier member and the annular wall of the cam member may be substantially concentric. The annular wall of the carrier member and the annular wall of the cam member may be substantially concentric with the turbine axis.

The cam member may be rotationally mounted on, and supported for rotation by, the carrier member. In this case, the carrier member may be mounted radially inwardly of the cam member. A radially inner surface of the cam member may bear against a radially outer surface of the annular wall of the carrier member, as the cam member rotates and/or as the carrier member moves axially. The at least one radially extending bore may extend radially inwardly from a first end, provided in a radially outer surface of the carrier member, to a second end.

Alternatively, the cam member may be mounted radially inwardly of the carrier member. In this case, the at least one radially extending bore may extend radially outwardly from a first end, provided in a radially inner surface of the carrier member, to a second end.

In each case, the second end of the bore may be closed, such that the bore is a blind bore.

The at least one coupling element may be elongate, having a longitudinal axis that is substantially parallel to the radial direction. The longitudinal axis of the at least one coupling element may be substantially straight.

The at least one coupling element may be a pin. The at least one coupling element may be substantially cylindrical.

The cam member may be rotationally mounted such that it is substantially fixed in the axial direction as it rotates. The cam member may be housed between first and second opposed radially extending surfaces that substantially fix the cam member in the axial direction as it rotates. The first and second radially extending surfaces may be a surface of a wall of the turbine housing and a surface of a wall of a bearing housing of the variably geometry turbine assembly respectively.

The annular wall of the cam member may have a radially inner and/or outer surface that extends substantially parallel to the axial direction.

The at least one slot in the annular wall of the cam member may extend substantially through the radial thickness of the annular wall.

The at least one slot in the annular wall of the cam member may be generally elongate, extending along a longitudinal axis. The longitudinal axis of the at least one slot may be inclined at a substantially constant angle relative to the radial plane. In this respect, the radial plane is a plane that is substantially perpendicular to the turbine axis. The longitudinal axis of the at least one slot may be inclined at an angle relative to the radial plane that varies along its length. This is advantageous in that it allows for a desired axial movement of the movable wall member for a certain rotational movement of the cam member. In this case, the angle of the longitudinal axis relative to the radial plane may decrease from a first end of the slot to a second end of the slot such that the at least one slot forms a concave curve. The angle of the longitudinal axis relative to the radial plane may increase and then decrease from a first end of the slot to a second end of the slot such that the at least one slot forms a curved wave shape.

A surface of the wall member that defines the at least one axially extending slot in the wall member may be arranged such that as the at least one surface of the annular wall member of the cam member that defines the at least one slot acts on the at least one coupling element to move the at least one coupling element in the axial direction, along the at least one axially extending slot in the wall member, the surface of the wall member that defines the at least one axially extending slot reacts the force applied to the at least one coupling element by the at least one surface of the annular wall member of the cam member that defines the at least one slot such that the at least one coupling element is moved in the axial direction along the axially extending slot.

The at least one axially extending slot may extend along a longitudinal axis that does not extend in the circumferential direction (i.e. the circumferential direction relative to the turbine axis). The at least one axially extending slot may be substantially straight in the axial direction.

Optionally the at least one axially extending slot has a width in the circumferential direction that is substantially equal to, or slightly greater than, the width of the at least one coupling element in the circumferential direction such that the at least one coupling element is prevented from moving in the circumferential direction as it moves along the at least one axially extending slot. The variable geometry turbine assembly may comprise an annular wall member, wherein the cam member is mounted radially inwardly of the annular wall member such that a radially outer surface of the annular wall of the cam member is opposed and adjacent to a radially inner surface of the annular wall member. The radially outer surface of the annular wall of the cam member may bear against the radially inner surface of the annular wall member as the cam member rotates.

The wall member that is provided with said at least one axially extending slot may be a wall member of a bearing housing of the variable geometry turbine assembly. Alternatively, said housing may be any other housing of the variable geometry turbine assembly.

The wall member that is provided with said at least one axially extending slot may be said annular wall member.

The at least one slot provided in the annular wall of the cam member, the at least one radially extending bore provided in the annular wall of the carrier member, the at least one axial slot provided in said wall member and the at least one coupling element may be a plurality of said slots, radially extending bores, axial slots and coupling elements respectively, wherein each coupling element is received in a respective said radially extending bore in the carrier member, in a respective said slot in the annular wall of the cam member and in a respective said axially extending slot in said wall member. The plurality of radially extending bores in the annular wall of the carrier member may be distributed in the circumferential direction about the annular wall of the carrier member.

The plurality of slots in the annular wall of the cam member may be distributed in the circumferential direction about the annular wall of the cam member.

The plurality of axially extending slots in the wall member may be distributed in the circumferential direction about said wall member. The variable geometry turbine assembly may further comprise a support member comprising an annular wall, wherein the carrier member is axially slidably mounted on a radially outer surface of the annular wall of the support member. The carrier member may be mounted directly on the support member.

The radially inner and/or radially outer surface of the annular wall of the support member may extend substantially parallel to the axial direction.

The support member may be made of stainless steel.

The support member and/or the carrier member may be provided with a coating that acts to reduce friction between the carrier member and the support member. Additionally, or alternatively, the support member may be provided with a coating of a material that is resistant to wear. The coating may be CM1 1 . The support member and/or carrier member may be subjected to a boronised surface treatment.

The support member may be substantially fixed in the axial direction. The support member may be mounted on and fixed to a housing of the variable geometry turbine assembly. The housing may be a bearing housing.

At least one sealing element may be provided between the support member and the housing so as to provide a seal between the support member and the housing. The housing may be a bearing housing. The at least one sealing element may be an annular seal. The at least one sealing element may extend substantially around the inner circumference of the support member. The at least one sealing element may be fixedly attached to the support member or the housing. The at least one sealing element may be mounted in a circumferential groove defined in the housing or in the support member.

At least one sealing element may be provided between the carrier member and the support member so as to provide a seal between the carrier member and the support member as the carrier member moves axially relative to the support member. The at least one sealing element may be an annular seal. The at least one sealing element may extend substantially around the inner circumference of the carrier member. The at least one sealing element may be fixedly attached to the carrier member. The at least one sealing element may be mounted in a circumferential groove defined in the carrier member. Alternatively, the at least one sealing element may be fixedly attached to the support member. In this case, the at least one sealing element may be mounted in a circumferential groove defined in the support member.

Instead of being axially slidably mounted a support member, the carrier member may be axially slidably mounted on a housing of the variable geometry turbine assembly, such as a bearing housing.

The variable geometry turbine assembly may comprise a nozzle ring. The nozzle ring may be provided with a plurality of guide vanes distributed circumferentially about the nozzle ring that extend into the annular inlet passageway. Each guide vane may extend from a root to a tip.

The nozzle ring may be axially fixed relative to the facing wall of the housing. The nozzle ring may be axially and/or rotationally fixed to the support member. The variable geometry turbine assembly may comprise an annular shroud. The annular shroud may comprise an annular wall provided with a plurality of slots, wherein each slot is arranged to receive a respective guide vane of the nozzle ring as the shroud is moved axially relative to the nozzle ring. The moveable wall member may be the annular wall of a shroud.

The variable geometry turbine assembly may comprise a biasing member arranged to bias the tips of the guide vanes into contact with the facing wall of the housing. The biasing member may be a resiliently deformable annular member.

Alternatively, the movable wall member may be the nozzle ring. In this case the facing wall of the housing may be the annular wall of the shroud.

The actuation mechanism may be provided on the same axial side of the annular inlet passageway as the movable wall member. Alternatively, the actuation mechanism may be provided on the opposite axial side of the annular inlet passageway to the movable wall member.

The actuation mechanism may be mounted on the same side of the annular inlet passageway as a bearing housing of the variable geometry turbine assembly. Alternatively, the actuation mechanism may be mounted on the same side of the annular inlet passageway as the turbine housing.

The actuation mechanism may be mounted between a bearing housing and a turbine housing of the variable geometry turbine assembly.

The facing wall of the housing may be a wall of the turbine housing. Alternatively, the facing wall of the may be a wall of any other housing of the variably geometry turbine assembly, including a wall of a bearing housing.

The variable geometry turbine assembly may further comprise an actuator coupled to the cam member so as to rotate the cam member about the turbine axis. The actuator may be coupled to the cam member by rotatable arm, wherein the cam member is provided with a formation that engages with the arm such that rotation of the arm by the actuator rotates the cam member about the turbine axis. The formation may be a radially extending protrusion that defines a cavity for receipt of the arm.

The actuator may be any suitable actuator, including an electrical, pneumatic or hydraulic actuator.

The carrier member may be provided with at least one recessed portion so as to provide clearance for the rotation of the arm. The recess may be in the radial and/or axial directions. The carrier member may be provided with a plurality of said recessed portions distributed in the circumferential direction.

Where the nozzle ring is axially fixed, the nozzle ring may comprise a heat shield integrally formed with the nozzle ring and disposed between the turbine wheel and a component of the variable geometry turbine assembly, arranged to protect said component from the hot gases in the turbine. The heat shield may be formed by a radially inner section of the nozzle ring, disposed between the turbine wheel and said component of the variable geometry turbine assembly. The heat shield section may be made of a heat resistant material, including stainless steel (e.g. 304 or pl33), Inconel or any suitable heat resistant material.

The carrier member, movable wall member, cam member and the at least one coupling element may form a cartridge assembly. Where the variable geometry turbine assembly comprises said support member, the support member and optionally the nozzle ring may also form part of the cartridge assembly.

A wall member of the variably geometry turbine assembly may be provided with a formation that is arranged to engage with a complimentary formation on nozzle ring, the carrier member, the cam member and/or the support member such that when the formations are engaged, the nozzle ring, carrier member, cam member and/or the support member is in a specific rotational orientation about the turbine axis.

The formation and complimentary formation may be a recess and protrusion, or vice versa. The wall member may be a wall member of a bearing housing.

Any of the features of the fourth aspect of the invention may be combined with any of the features of any of the preceding aspects of the invention, in any combination. Similarly, any of the features of the preceding aspects of the invention may be combined with any of the features of the fourth aspect of the invention, in any combination.

A preferred embodiment of the variable geometry turbine assembly of the fourth aspect of the invention is the first embodiment of the invention shown in Figures 1 to 24c. The variable geometry turbine assembly of the fourth aspect of the invention may have any of the features of the first embodiment.

An actuator may be coupled to the cam member so as to rotate the cam member. The actuator may be any suitable actuator, including a pneumatic, hydraulic or electric actuator. According to a fifth aspect of the invention there is provided an actuation mechanism assembly comprising an actuation mechanism for moving a movable wall member, a surface of which defines, with a facing wall, an annular inlet passageway of a turbine, so as to vary the width of the annular inlet passageway, the actuation mechanism comprising: a carrier member, the carrier member being movable in an axial direction and coupled to the movable wall member such that as the carrier member is moved in the axial direction, the moveable wall member is moved in the axial direction a cam member provided with at least one formation; the carrier member being coupled to at least one co-operating formation such that as the at least one co-operating formation is moved in the axial direction, the carrier member is moved in the axial direction, wherein one of the at least one formation and the at least one co-operating formation is a radially extending formation and the other defines a complimentary recess for receiving the radially extending formation, the at least one formation or the at least one co-operating formation extending in both the circumferential direction and the axial direction; the actuation mechanism is arranged such that as the cam member is rotated relative to the carrier member, the at least one formation and the at least one cooperating formation engage such that the at least one co-operating formation is moved in the axial direction, thereby moving the carrier member in the axial direction, and thereby moving the movable wall member in the axial direction so as to vary the size of the inlet passageway; the actuation member assembly further comprising a nozzle ring having a plurality of circumferentially distributed inlet vanes and an annular shroud provided with a plurality of slots for receiving the inlet vanes of the nozzle ring as the shroud is moved axially relative to the nozzle ring; wherein the shroud comprises the movable wall member; and the nozzle ring and shroud are mountable on the same axial side of the inlet passageway.

According to a sixth aspect of the invention there is provided an actuation mechanism for moving a movable wall member, a surface of which defines, with a facing wall, an annular inlet passageway of a turbine, so as to vary the width of the annular inlet passageway, the actuation mechanism comprising: an annular carrier member, the carrier member being movable in an axial direction and for coupling to the movable wall member such that as the carrier member is moved in the axial direction, the moveable wall member is moved in the axial direction a cam member mounted for rotation; the cam member is provided with at least one formation; the carrier member being coupled to at least one co-operating formation such that as the at least one co-operating formation is moved in the axial direction, the carrier member is moved in the axial direction, wherein one of the at least one formation and the at least one co-operating formation is a radially extending formation and the other defines a complimentary recess to receive the radially extending formation, the at least one formation extending in both the circumferential direction and the axial direction; the actuation mechanism is arranged such that as the cam member is rotated, the at least one formation and the at least one co-operating formation engage such that the at least one co-operating formation is moved in the axial direction, thereby moving the carrier member in the axial direction, and thereby moving the movable wall member in the axial direction so as to vary the size of the inlet passageway; wherein the cam member and the carrier member axially overlap for at least one axial position of the movable wall member. According to a seventh aspect of the invention there is provided there is provided an actuation mechanism assembly comprising an actuation mechanism and a movable wall member, wherein the actuation mechanism is for moving the movable wall member, a surface of which defines, with a facing wall, an annular inlet passageway of a turbine, so as to vary the width of the annular inlet passageway, the actuation mechanism comprising: a carrier member, the carrier member being movable in an axial direction and coupled to the movable wall member such that as the carrier member is moved in the axial direction, the moveable wall member is moved in the axial direction a cam member provided with at least one formation; the carrier member being coupled to at least one co-operating formation such that as the at least one co-operating formation is moved in the axial direction, the carrier member is moved in the axial direction, wherein one of the at least one formation and the at least one co-operating formation is a radially extending formation and the other defines a complimentary recess for receiving the radially extending formation, the at least one formation or the at least one co-operating formation extending in both the circumferential direction and the axial direction; the actuation mechanism is arranged such that as the cam member is rotated relative to the carrier member, the at least one formation and the at least one cooperating formation engage such that the at least one co-operating formation is moved in the axial direction, thereby moving the carrier member in the axial direction, and thereby moving the movable wall member in the axial direction so as to vary the size of the inlet passageway; wherein the cam member is disposed radially outwardly of the movable wall member.

According to an eighth aspect of the invention there is provided an actuation mechanism for moving a movable wall member, a surface of which defines, with a facing wall of a housing, an annular inlet passageway of a turbine, so as to vary the width of the annular inlet passageway, the actuation mechanism comprising: a carrier member for coupling to a movable wall member, a surface of which defines, with a facing wall of a housing, an annular inlet passageway of a turbine, such that as the carrier member is moved in the direction of a longitudinal axis of the carrier member, the moveable wall member is moved in the axial direction, the carrier member having an annular wall provided with at least one radially extending bore; at least one radially extending coupling element being received in the at least one radially extending bore in the annular wall of the carrier member such that as the at least one coupling element is moved in the axial direction, the carrier member is moved in the axial direction; a cam member mounted for rotation about said axis, the cam member having an annular wall provided with at least one slot defined by at least one surface of the annular wall, the at least one slot extending in both the circumferential direction and the axial direction; the at least one coupling element also being received in the at least one slot in the cam member; the at least one coupling element being for receipt in at least one axially extending slot in a wall member such that as the cam member is rotated about said axis, the at least one slot in the annular wall of the cam member is moved relative to the at least one coupling element, with the at least one surface of the cam member that defines the at least one slot acting on the at least one coupling element to move the at least one coupling element in a the axial direction, along the at least one axially extending slot in said wall member, thereby moving the carrier member in the axial direction and thereby moving the movable wall member in the axial direction, so as to vary the width of the inlet passageway.

According to a ninth aspect of the invention there is provided a turbomachine comprising a variable geometry turbine assembly according to any of the first to the fourth aspects of the invention. The turbomachine may comprise a bearing housing arranged to house at least one bearing that rotatably supports a shaft on which the turbine wheel is mounted and wherein the wall member provided with the at least one axially extending slot is a wall member of the bearing housing.

The turbomachine may be a turbocharger, wherein the turbine wheel is mounted on a shaft, the turbocharger comprising a compressor having an impeller wheel rotatably mounted within a compressor housing and coupled to the shaft such that rotation of the turbine wheel rotates the compressor wheel thereby drawing air in through an inlet of the compressor, compressing the air and passing it to an outlet of the compressor.

Any features of any of the above aspects of the invention may be combined with any features of any other aspect of the invention in any combination. In this regard, the actuation mechanism of any of the fifth to the eighth aspects of the invention may have any feature of the variable geometry turbine assembly of any preceding aspect of the invention.

Specific embodiments of the present invention will now be described, by way of example only, with reference to the accompanying drawings, in which:

Figure 1 is an axial cross section through a variable geometry turbocharger according to a first embodiment of the present invention; Figure 2 is an exploded perspective view of part of a variable geometry turbine and of a bearing housing of the variable geometry turbocharger shown in figure 1 ;

Figure 3 is a view corresponding to that of Figure 2, but with a circumferential section cut away for illustrative purposes;

Figure 4 is an axial cross-section through a cam member, carrier member, support member, shroud and nozzle ring of the variable geometry turbine shown in figures 1 to 3; Figure 5 is a rear perspective view of a cam member of the variable geometry turbine shown in figures 1 to 3;

Figure 6 is a front perspective view of a nozzle ring of the variable geometry turbine shown in figures 1 to 3;

Figure 7 is an axial cross-sectional view of the nozzle ring shown in figure 6;

Figure 8 is a rear perspective view of the nozzle ring shown in figures 6 and 7;

Figure 9 is a front perspective view of a support member of the variable geometry turbine shown in figures 1 to 3;

Figure 10 is an axial cross-sectional view of the support member shown in figure 9;

Figure 1 1 is a front perspective view of a shroud of the variable geometry turbine shown in figures 1 to 3;

Figure 12 is an axial cross-sectional view of the shroud shown in figure 1 1 ;

Figure 13 is a rear perspective view of the shroud shown in figures 1 1 and 12;

Figure 14 is a front perspective view of a carrier member of the variable geometry turbine shown in figures 1 to 3;

Figure 15 is an axial cross-sectional view of the carrier member shown in figure 14;

Figure 16 is a rear perspective view of the carrier member shown in figures 14 and 15; Figure 17 is a rear perspective view of a bearing housing of the turbocharger shown in figures 1 to 3;

Figure 18 is an axial cross-sectional view of the bearing housing shown in figure 17; Figure 19 is a front perspective view of the bearing housing shown in figures 17 and 18;

Figure 20 is an enlarged perspective view of the region labelled 'A' in Figure 19;

Figure 21 is a cut away perspective view of a turbine housing of the turbocharger shown in figures 1 to 3;

Figure 22 is a perspective view of a rotatable arm assembly of the turbocharger shown in figures 1 to 3;

Figure 23 is a cut away perspective view of the rotatable arm assembly shown in figure 22, Figure 24a is a side elevational view of the cam member shown in Figure 5;

Figures 24b and 24c are views corresponding to that of Figure 24a but where the slots in the annular wall of the cam member are of a different shape (where the shape of the slots is shown as a thicker darker line overlying the slot of Figure 24a);

Figure 25 is an axial cross section through a variable geometry turbocharger according to a second embodiment of the present invention;

Figure 26 is an exploded perspective view of part of a variable geometry turbine and of a bearing housing of the variable geometry turbocharger shown in figure 25;

Figure 27 is a view corresponding to that of Figure 26, but with a circumferential section cut away for illustrative purposes; Figure 28 is an axial cross-section through a cam member, carrier member, support member, shroud and nozzle ring of the variable geometry turbine shown in figures 25 to 27;

Figure 29 is a rear perspective view of a cam member of the variable geometry turbine shown in figures 25 to 27; Figure 30 is a front perspective view of a nozzle ring of the variable geometry turbine shown in figures 25 to 27; Figure 31 is an axial cross-sectional view of the nozzle ring shown in figure 30;

Figure 32 is a rear perspective view of the nozzle ring shown in figures 30 and 31 ;

Figure 33 is a front perspective view of a support member of the variable geometry turbine shown in figures 25 to 27;

Figure 34 is an axial cross-sectional view of the support member shown in figure 33;

Figure 35 is a front perspective view of a shroud of the variable geometry turbine shown in figures 25 to 27;

Figure 36 is an axial cross-sectional view of the shroud shown in figure 35;

Figure 37 is a rear perspective view of the shroud shown in figures 35 and 36;

Figure 38 is a front perspective view of a carrier member of the variable geometry turbine shown in figures 25 to 27;

Figure 39 is an axial cross-sectional view of the carrier member shown in figure 38;

Figure 40 is a rear perspective view of a bearing housing of the turbocharger shown in figures 25 to 27;

Figure 41 is an axial cross-sectional view of the bearing housing shown in figure 40;

Figure 42 is a front perspective view of the bearing housing shown in figures 40 and 41 ;

Figure 43 is an enlarged perspective view of the region labelled 'A' in Figure 42; Figure 44 is a cut away perspective view of a turbine housing of the turbocharger shown in figures 25 to 27;

Figure 45 is a perspective view of a rotatable arm assembly of the turbocharger shown in figures 25 to 27;

Figure 46 is a cut away perspective view of the rotatable arm assembly shown in figure 45; Figure 47 is an axial cross section through a variable geometry turbocharger according to a third embodiment of the present invention;

Figure 48 is an exploded perspective view of part of a variable geometry turbine and of a bearing housing of the variable geometry turbocharger shown in figure 47;

Figure 49 is a view corresponding to that of Figure 48, but with a circumferential section cut away for illustrative purposes;

Figure 50 is an axial cross-section through a carrier member, support member, shroud and nozzle ring of the variable geometry turbine shown in figures 47 to 49;

Figure 51 is a rear perspective view of a cam member of the variable geometry turbine shown in figures 47 to 49; Figure 52 is a front perspective view of a nozzle ring of the variable geometry turbine shown in figures 47 to 49;

Figure 53 is an axial cross-sectional view of the nozzle ring shown in figure 52; Figure 54 is a rear perspective view of the nozzle ring shown in figures 52 and 53;

Figure 55 is a front perspective view of a support member of the variable geometry turbine shown in figures 47 to 49; Figure 56 is an axial cross-sectional view of the support member shown in figure 55; Figure 57 is a rear perspective view of the support member shown in figures 55 and 56;

Figure 58 is an exploded perspective view, with a circumferential section cut away for illustrative purposes, of a section of a bearing housing and the support member of the variable geometry turbine shown in figures 47 to 49, showing how the support member is slidably mounted to the bearing housing;

Figure 59 is a front perspective view of a shroud of the variable geometry turbine shown in figures 47 to 49;

Figure 60 is an axial cross-sectional view of the shroud shown in figure 59;

Figure 61 is a rear perspective view of the shroud shown in figures 59 and 60;

Figure 62 is a front perspective view of a carrier member of the variable geometry turbine shown in figures 47 to 49;

Figure 63 is an axial cross-sectional view of the carrier member shown in figure 62;

Figure 64 is a rear perspective view of a carrier member shown in Figures 62 and 63;

Figure 65 is a rear perspective view of a bearing housing of the turbocharger shown in figures 47 to 49;

Figure 66 is an axial cross-sectional view of the bearing housing shown in figure 65;

Figure 67 is a front perspective view of the bearing housing shown in figures 65 and 66;

Figure 68 is a cut away perspective view of a turbine housing of the turbocharger shown in figures 47 to 49;

Figure 69 is a perspective view of a rotatable arm assembly of the turbocharger shown in figures 47 to 49; Figure 70 is a cut away perspective view of the rotatable arm assembly shown in figure 69; Figure 71 is an axial cross section through a variable geometry turbocharger according to a fourth embodiment of the present invention;

Figure 72 is an exploded perspective view of part of a variable geometry turbine and of a bearing housing of the variable geometry turbocharger shown in figure 71 ;

Figure 73 is a view corresponding to that of Figure 72, but with a circumferential section cut away for illustrative purposes;

Figure 74 is an axial cross-section through a carrier member, support member, shroud and nozzle ring of the variable geometry turbine shown in figures 71 to 73;

Figure 75 corresponds to Figure 74 but in exploded form;

Figure 76 is a rear perspective view of a cam member of the variable geometry turbine shown in figures 71 to 73;

Figure 77 is a front perspective view of a nozzle ring of the variable geometry turbine shown in figures 71 to 73; Figure 78 is an axial cross-sectional view of the nozzle ring shown in figure 77;

Figure 79 is a rear perspective view of the nozzle ring shown in figures 77 and 78;

Figure 80 is a front perspective view of a support member of the variable geometry turbine shown in figures 71 to 73;

Figure 81 is an axial cross-sectional view of the support member shown in figure 80;

Figure 82 is a front perspective view of a radial wall of shroud of the variable geometry turbine shown in figures 71 to 73; Figure 83 is a rear perspective view of the radial wall of the shroud shown in figure 82;

Figure 84 is an axial cross-sectional view of the radial wall of the shroud shown in figures 82 and 83;

Figure 85 is a front perspective view of a radially inner axially extending annular flange of the shroud of the variable geometry turbine shown in figures 71 to 73; Figure 86 is an axial cross-sectional view of the radially inner axially extending annular flange of the shroud shown in figure 85;

Figure 87 is a front perspective view of a radially outer axially extending annular flange of the shroud of the turbocharger shown in Figures 71 to 73;

Figure 88 is an axial cross-sectional view of the radially outer axially extending annular flange of the shroud shown in Figure 87;

Figure 89 is a rear perspective view of radially outer, axially extending annular flange of the shroud shown in Figures 87 and 88;

Figure 90 is a rear perspective view of a bearing housing of the turbocharger shown in figures 71 to 73; Figure 91 is an axial cross-sectional view of the bearing housing shown in figure 90;

Figure 92 is a front perspective view of a bearing housing of the turbocharger shown in figures 90 and 91 ; Figure 93 is a cut away perspective view of a turbine housing of the turbocharger shown in figures 71 to 73;

Figure 94 is a perspective view of a rotatable arm assembly of the turbocharger shown in figures 71 to 73, and Figure 95 is a cut away perspective view of the rotatable arm assembly shown in figure 94.

Referring to Figures 1 to 24 there is shown a variable geometry turbocharger 1 comprising a variable geometry turbine assembly according to a first embodiment of the present invention. The variable geometry turbocharger 1 comprises a variable geometry turbine 61 connected to a compressor 92 by a bearing assembly 93.

In more detail, the variable geometry turbine 91 comprises a turbine housing 2 that is connected to a compressor housing 3 of the compressor 92 by a central bearing housing 4 of the bearing assembly 93.

The turbocharger 1 has a turbocharger axis 5a. The turbocharger 1 is generally symmetric about the turbocharger axis 5a. The variable geometry turbine 91 has a turbine axis 105a, which is coincident with and substantially parallel to the turbocharger axis 5a.

It will be appreciated that, unless otherwise stated, references to 'radially extending', 'radial', 'axially extending', 'axial, 'circumferentially extending' and 'circumferential' are in relation to the turbocharger axis 5a (and therefore also the turbine axis 105a).

A turbocharger shaft 5 extends from the turbine housing 2 to the compressor housing 3 through the bearing housing 4. A turbine wheel 6 is mounted on one end of the shaft 5 for rotation within the turbine housing 2 about the turbocharger axis 5a. The compressor wheel 7 is mounted on the other end of the shaft 5 for rotation within the compressor housing 3. The shaft 5 rotates about the turbocharger axis 5a and is supported for rotation by bearings 94 located in the bearing housing 4.

The turbine housing 2 defines an inlet volute 8 to which gas from an internal combustion engine (not shown) is delivered. The exhaust gas flows from the inlet volute 8 to an axial outlet passageway 9 via an annular inlet passageway 10 and the turbine wheel 6.

References to 'inboard' and 'outboard' are in relation to the annular inlet passageway 10. Gas flowing from the inlet volute 8 to the outlet passageway 9 passes over the turbine wheel 6 and as a result torque is applied to the shaft 5 to drive the compressor wheel 7. Rotation of the compressor wheel 7 within the compressor housing 3 pressurises ambient air in an axial inlet 101 defined by the compressor housing 3 and delivers the pressurised air to an annular outlet volute 102 from which it is fed to an internal combustion engine (not shown). Details of the compressor 92 may be entirely conventional (for instance they may correspond to those of a known compressor) and therefore will not be described in further detail.

The inboard portion 1 10 of the bearing housing 4 (see below) and the turbine 91 together form a variable geometry turbine assembly according to a first embodiment of the invention. The present invention is suitable for, but not limited to, a turbocharger. However, since the invention relates to the nature of a variable geometry turbine assembly, other details of a turbocharger incorporating the variable geometry turbine assembly of the present invention, such as other details of the bearing housing 4 and the compressor 3 will not be described in any further detail.

The turbine housing 2 comprises an inlet portion 120 and an outlet portion 121 which define the inlet volute 8 and the axial outlet passageway 9 respectively. The inlet portion 120 is attached to an axially inboard portion 1 10 (see figure 18) of the bearing housing 4 by a plurality of circumferentially spaced bolts 1 12. It will be appreciated that the turbine housing 2 may be fixedly attached to the bearing housing 4 by any suitable means of attachment, including by a V- band.

An annular cavity 24 is defined between the inboard section 1 10 of the bearing housing 4 and the inlet portion 120 of the turbine housing 2. The annular cavity 24 is substantially centred on the turbocharger axis 5a.

The variable geometry turbine 91 comprises an annular shroud 1 1 (as shown in more detail in figures 1 1 to 13). The shroud 1 1 is generally annular and is substantially centred on the turbocharger axis 5a. The shroud 1 1 comprises a radial annular wall 18 that has a radial inboard surface 12 and a radial outboard surface 20. The inboard and outboard radial surfaces 12, 20 are generally annular, are substantially centred on the turbocharger axis 5a and extend in the radial direction, substantially perpendicular to the turbocharger axis 5a. The annular wall 18 is provided with a plurality of slots 16, wherein each slot 16 is arranged to receive a respective guide vane 15 of the nozzle ring 13 as the shroud 1 1 is moved axially relative to the nozzle ring 13 (see below).

The annular wall 18 forms a movable wall member to vary the width of the inlet passageway (as described in more detail below).

The shroud 1 1 further comprises an axially extending annular flange 19 that extends, in the axially outboard direction, away from the outer radial periphery of the axially outboard surface 20 of the shroud 1 1 . The axially extending annular flange 19 is substantially parallel to the turbocharger axis 5a. The axially extending flange 19 has a section 23 towards its outboard end that is of reduced thickness, such that it defines an annular step.

The annular inlet passageway 10 is defined between the axially inboard surface 12 of the shroud 1 1 and a facing inboard surface 17 of the turbine housing 2. The facing inboard surface 17 of the turbine housing 2 is generally annular, is substantially centred on the turbocharger axis 5a and extends in the radial direction, substantially perpendicular to the turbocharger axis 5a. As will be described in more detail below, the shroud 1 1 is axially slidably mounted within the cavity 24, for axial movement relative to the inboard surface 17 of the turbine housing 2, so as to vary the width of the inlet passageway 10.

In this respect, the width of the inlet passageway 10 is varied to optimise gas flow velocities over a range of mass flow rates so that the power output of the turbine 91 can be varied to suit varying engine demands. For instance, when the volume of exhaust gas being delivered to the turbine 91 is relatively low, the velocity of the gas reaching the turbine wheel 6 is maintained at a level which ensures efficient turbine operation by reducing the size of the annular inlet passageway 10. The inboard surface 12 (and the outboard surface 20) of the radial wall 18 of shroud 1 1 is provided on the same axially inboard side of the annular inlet passageway 10 as the bearing housing 4. The variable geometry turbine 91 further comprises a fixed nozzle ring 13 (as shown in more detail in figures 6 to 8), mounted within the cavity 24. The nozzle ring 13 is located within the radially outer, axially extending flange 19 of the shroud 1 1 .

The nozzle ring 13 is generally annular and is substantially centred on the turbocharger axis 5a. The nozzle ring 13 comprises an annular radially extending wall 25 having an axially inboard surface 14 and an axially outboard surface 26. The inboard and outboard surfaces 14, 26 extend in the radial direction, substantially perpendicular to the turbocharger axis 5a. A plurality of circumferentially distributed inlet vanes 15 extend axially inboard from the inboard surface 14, into the annular inlet passageway 10. The vanes 15 each extend axially inboard from a root, at said inboard surface 14, to a tip, distal to said inboard surface 14. The inlet vanes 15 are arranged so as to deflect gas flowing through the inlet passageway 10 towards the direction of rotation of the turbine wheel 6.

In this respect, the radially extending wall 25 of the nozzle ring 13 is disposed axially outboard of the radial wall 18 of the shroud 1 1 , with the inlet vanes 15 of the nozzle ring 13 extending through axial slots 16 in the radial wall 18 of the shroud 1 1 , into the annular inlet passageway 10.

The nozzle ring 13 is fixed, both axially and rotationally, to the bearing housing 4. In this respect, an annular flange 28 extends from a radially outer section of the outboard surface 26 of the nozzle ring 13 in the axially outboard direction. A radially inner surface of the axially extending flange 28 is mounted on a radially outer surface 27 (see Figure 1 ) of the inboard portion 1 10 of the bearing housing 4.

The nozzle ring 13 comprises an integral heat shield 31 formed by a radially inner annular portion of the nozzle ring 13. The heat shield 31 of the nozzle ring 13 extends radially inwardly from a radially inner section of the inboard surface 14 of the radial wall 25 of the nozzle ring. The heat shield 31 is bent in the axial and radial directions to form an axial section 31 1 and a radial section 312. The axial section 31 1 extends from the radially inner periphery of the radial wall 25 of the nozzle ring 13, in the axially inboard direction. The radial section 312 is substantially axially aligned with the inboard surface 12 of the shroud 1 1 . The radial section 312 extends radially inwardly, from an inboard end of the axial section 31 1 , to substantially cover the region of the bearing housing 4 between the bearing housing 4 and the turbine wheel 6. Accordingly, the heat shield 31 protects this section of the bearing housing 4 from the hot exhaust gases in the turbine 2. The heat shield is made of a heat resistant material in the form of stainless steel (e.g. 304 or pl33) or Inconel. It will be appreciated that any suitable heat resistant material may be used. The nozzle ring 13 is axially fixed to a support member 32, as described in more detail below.

The support member 32 is a substantially annular ring that is centred on the turbocharger axis 5a. The support member 32 is shown in more detail in figures 4, 9 and 10.

The support member 32 comprises a generally annular wall member 131 having radially inner and outer annular surfaces 34, 33 respectively. The annular wall member 131 (and the radially inner and outer surfaces 34, 33) extend substantially parallel to the axial direction 5a.

The support member 32 is substantially fixed in the axial direction. In this regard, the radially inner surface 34 of the support member 32 is mounted on and axially (and rotationally) fixed to the radially outer surface 27 of the bearing housing 4.

The support member 32 is mounted on the bearing housing 4 with a slight radial clearance from the radially outer surface 27 of the bearing housing in order to ensure an axial sliding fit, for assembly. Tolerancing is applied to minimise 'slop' between these two components due to thermal expansion. The radially inner surface 34 is provided, substantially midway along its axial length, with a radially inwardly extending annular flange 35. The support member 32 is mounted on the radially outer surface 27 of the inboard portion 1 10 of the bearing housing 4. In more detail, a radially inner surface 132 of the annular flange 35 is mounted on said radially outer surface 27 of the bearing housing 4. The support member 32 is mounted within the cavity 24, axially outboard of the radial wall 25 of the nozzle ring 13. The annular flange 35 and the radially inner surface 34 of the support member 32 form a stepped arrangement that is welded to a complimentary stepped arrangement formed by the radially outer surface 29, and an axially outboard end, of the axially extending flange 28 of the nozzle ring 13. In this way, the nozzle ring 13 is fixedly attached, both axially and rotationally, to the support member 32. It will be appreciated that the nozzle ring 13 may be fixedly attached to the support member 32 by any suitable means, including brazing. An annular groove 36 is provided in the radially outer surface 27 of the inboard portion 1 10 of the bearing housing 4 (see Figure 1 ). An annular ring seal 37 is located within the annular groove 36 and provides a seal between the radially outer surface 27 of the bearing housing 4 and the radially inner surface 132 of the annular flange 35 of the support member 32. This sealing arrangement prevents gas from flowing from the annular inner passageway 10, passed the ring seal 37. This facilitates the maintenance of a desired pressure differential across the radial wall 18 of the shroud 1 1. The seal 37 stops flow of gas into the cavity 24 between bearing housing and nozzle ring, maintaining the pressure differential for load balance.

A resiliently deformable annular tolerance ring 38 (see Figures 1 and 2) is sandwiched between the axially outboard side of the annular flange 35 of the support member 32 and an opposed surface of the bearing housing 4. The tolerance ring 38 provides an axially force inboard force to the nozzle ring 13 via the support member 32. In this regard, as the turbine housing 2 is bolted onto the bearing housing 4, the facing wall 17 of the turbine housing 2 exerts a force on the tips of the inlet vanes 15, and therefore the nozzle ring 13, in the direction away from said facing wall 17, which acts to compress the tolerance ring 38. This pre-loads the tolerance ring 38, which causes it to exert a force in the opposite direction on the nozzle ring 13 via the support member 32, which is free floating on the bearing housing 4. In this regard, the support member 32 is slidable mounted on the bearing housing 4. This ensures that contact is maintained between the tips of the inlet vanes 15 and said facing wall 14 regardless of turbine gas pressure & pulsations. This also minimises the flow of gas over the tips of the vanes 15 at small diffuser passageway 10 widths, thereby improving efficiency.

The inboard surface 14 of a radially outer section of the annular wall 25 of the nozzle ring 13 acts a stop that limits the axial position, in the outboard direction, of the shroud 11 . In this regard, as the shroud 1 1 moves in the outboard direction (see below), the outboard surface 20 of the annular wall 18 of the shroud 1 1 abuts the inboard surface 14 of a radially outer section of the annular wall 25 of the nozzle ring 13, thereby acting as a stop to provide a desired maximum outboard position of the shroud 1 1 .

The shroud 1 1 is moved in the axial direction, to vary the width of the annular inlet passageway 10, by the use of an actuation mechanism, which will now be described in detail.

The actuation mechanism comprises a carrier member 39, as shown in more detail in figures 14 to 16. The carrier member 39 is a substantially annular ring that is substantially centred on the turbocharger axis 5a. The carrier member 39 comprises an annular wall 1 17 having radially inner and outer annular surfaces 40, 41 . The annular wall 1 17 extends substantially parallel to the axial direction 5a. In this regard, the radially inner and outer surfaces 40, 41 of the annular wall 1 17 extend substantially parallel to the axial direction 5a.

An annular flange 1 14 extends radially inwardly from the radially inner surface 40. The annular flange 1 14 is substantially perpendicular to the axial direction 5a. An annular groove 46 is provided in the annular flange 1 14.

The annular wall 1 17 has axially inboard and outboard sections 42, 45 disposed on inboard and outboard sides of the annular flange 1 14. The outboard section 45 is of greater thickness than the inboard section 42.

The carrier member 39 is fixed, both axially and rotationally, to the shroud 1 1 . Accordingly, as the carrier member 39 moves axially, the shroud 1 1 is moved axially with the carrier member 39. The carrier member 39 is fixed directly to the shroud 1 1 . In this respect, a radially inner surface of the inboard section 42 of the annular wall 1 17 is welded to a radially outer surface of the outboard section of reduced thickness 23 of the axial flange 19 of the shroud 1 1 . It will be appreciated that carrier member 39 may be fixedly attached to the shroud 1 1 by any suitable means, including brazing. The annular wall 1 17 is provided with a plurality of radial bores 43. Specifically, the annular wall 1 17 is provided with three radial bores 43 circumferentially distributed about the annular wall 1 17. The radial bores 43 are equally circumferentially spaced around the annular wall.

Each radial bore 43 extends radially inwardly from a first end provided in the radially outer surface 41 of the carrier member 39, along a longitudinal axis that is substantially parallel to the radial direction, to a second end. The longitudinal axis of each radially extending bore is substantially straight. Each radial bore 43 terminates before the radially inner surface 40 of the carrier member 39 so that its second end is closed and forms a blind bore 43. Each bore 43 has a substantially circular cross-sectional shape about its longitudinal axis. Each bore 43 is for receipt of a substantially cylindrical pin 69 (as discussed in more detail below).

The axially outboard section 45 of the annular wall 1 17 is provided with a plurality of axially extending recesses 44 distributed circumferentially about the annular wall 117. When the carrier member 39 is mounted in position, one of its recesses is adjacent to an arm 60 of a rotatable arm assembly 57 and provides clearance for the arm 60 to rotate, as described in more detail below.

The carrier member 39 is slidably mounted on the radially outer surface 33 of the support member 32 for movement in the axial direction. The carrier member 39 is mounted directly on the support member 32. In more detail, a substantially annular seal 44 is received within the annular groove 46 in the flange 1 14 of the carrier member 39 between the flange 1 14 and the radially outer surface 33 of the support member 32. The annular seal 44 seals the carrier member 39 against the support member 32 as the carrier member 39 moves axially relative to the support member 32. This prevents gases flowing from the annular inlet passageway 10 axially outboard of the carrier member 39, which helps to maintain a desired pressure differential across the carrier member 39.

The actuation mechanism further comprises a cam member 47, as shown in more detail in Figure 5. The cam member 47 is a substantially annular ring that is substantially centred on the turbocharger axis 5a. The cam member 47 comprises an annular wall 104 having radially inner and outer annular surfaces 49, 48. The annular wall 104 (and its radially inner and outer annular surfaces 49, 48) extends substantially parallel to the axial direction 5a.

A plurality of slots 50 are provided in the annular wall 104 and are defined by respective inner surfaces 51 of the annular wall 104. Each slot is generally elongate and extends along a longitudinal axis 50a (see Figures 5 and 24a). Each slot extends substantially through the radial thickness of the annular wall 104.

In the currently described embodiment there are three slots 50. Each slot 50 is substantially identical. The slots 50 are distributed in the circumferential direction around the annular wall 104, substantially equally spaced apart.

Each slot 50 extends in both the circumferential direction and the axial direction. In this respect, each slot 50 defines a part of a helix about the turbocharger axis 5a. Specifically, the longitudinal axis 50a of each slot 50 extends in both the circumferential direction and the axial direction 5a. In this respect, the longitudinal axis 50a of each slot 50 defines a part of a helix about the turbocharger axis 5a.

In the embodiment of the cam member 47 shown in Figures 5 and 24a, the longitudinal axis 50a of each slot 50 is inclined at a substantially constant angle relative to the radial plane. In this respect, the radial plane is a plane that is substantially perpendicular to the turbocharger axis 5a.

In the embodiment of the cam member 47 shown in Figures 24b and 24c, the longitudinal axis 50a of each slot 50 is inclined at an angle relative to the radial plane that varies along its length. This is advantageous in that it allows for a desired axial movement of the shroud 1 1 for a certain rotational movement of the cam member 47.

In the embodiment of Figure 24b, the angle of the longitudinal axis 50a relative to the radial plane decreases from a first end 501 of the slot 50 to a second end 502 of the slot 50 such that slot 50 forms a concave curve.

In the embodiment of Figure 24c, the angle of the longitudinal axis 50a relative to the radial plane increases and then decreases from the first end 501 of the slot 50 to the second end 502 of the slot 50 such that the slot 50 forms a curved wave shape. The cam member 47 is mounted for rotation about the turbocharger axis 5a. In this regard, the cam member 47 is rotatably mounted on, and radially outwardly of, the carrier member 39 and the axial extending flange 19 of the shroud 1 1 . In this respect, the radially inner surface 49 of the cam member 47 is mounted on the radially outer surface 41 of the annular wall of the carrier member 39 and on an axial portion of the radially outer surface 22 of the axially extending flange 19 of the shroud.

The radially inner surface 49 of the cam member 47 bears against the radially outer surface 41 of the annular wall of the carrier member 39, as the cam member 47 rotates and as the carrier member 39 moves axially.

The annular wall 1 17 of the carrier member 39 and the annular wall 104 of the cam member 47 are substantially concentric with the turbocharger axis 5a.

The cam member 47 is sandwiched between opposed radially extending annular surfaces 201 , 202 of the bearing housing 4 and turbine housing 2 respectively, such that the cam member 47 can rotate about the turbocharger axis 5a but is substantially fixed in the axial direction 5a, relative to the bearing and turbine housings 4, 2. The slots 50 have substantially corresponding circumferential positions to the radial bores 43 in the carrier member 39. Said radial surfaces 201 , 202 are substantially perpendicular to the axial direction 5a. The inboard portion 1 10 of the bearing housing 4 comprises an annular wall member 53. The annular wall member 53 has an axially inboard, radially extending annular surface 54. The surface 54 is substantially perpendicular to the axial direction 5a. An annular flange 52 extends axially inboard from the surface 54. The annular flange 52 has radially outer and inner surfaces 151 , 153. The annular flange 52 is substantially centred on the axis 5a of the turbocharger. A circumferentially extending gap 152 is provided in the annular flange 52 so as to allow clearance for rotation of an arm 60 of a rotatable arm assembly 57 (as described in more detail below).

A set of three axially extending slots 55 is provided in the axially extending flange 52, distributed circumferentially about the annular flange 52. Each axial slot 55 is defined by a respective inner surface 56 of the annular flange 52. Each axial slot 55 extends axially outboard from the axially inboard end of the annular flange 52, forming an open end at the outboard end of the annular flange 52. The slot 55 terminates within the axial extent of the annular flange 52 so as to form a blind slot 55. Each axial slot 55 extends throughout the thickness of the annular flange 52, from its radially inner surface 153 to its radially outer surface 151 . Each slot 55 is substantially straight in the axial direction 5a. The longitudinal axis of each slot 55 does not extend in the circumferential direction. The cam member 47 is mounted radially inwardly of the annular flange 52. In this respect, the radially outer surface 48 of the annular wall 104 of the cam member 47 is disposed radially inwardly of the radially inner surface 153 of the annular flange 52 of the bearing housing 4, with a small radial clearance provided between said surfaces 48, 153. The arrangement is such as to allow for the rotation of the cam member 47 relative to the bearing housing 4. Alternatively the radially outer surface 48 of the annular wall 104 of the cam member 47 may bear against the radially inner surface 153 of the annular flange 52 of the bearing housing 4.

The actuation mechanism further comprises a set of three pins 69. Each pin 69 is generally elongate, extending along a longitudinal axis 1 18. Each pin 69 is substantially straight. The longitudinal axis 1 18 of each pin is substantially straight and is substantially parallel to the radial direction. Each pin 69 has a substantially circular cross-sectional shape about its longitudinal axis.

Each pin 69 is received within a respective said radial bore 43 in the carrier member 39. Each pin 69 is axially fixed relative to the carrier member 39. In this respect, each radially extending bore 43 has an axial extent that is substantially the same as, or slightly greater than, the axial extent of the respective pin 69 such that as the pin 69 is moved in the first and second axial directions, the carrier member 39 is moved in the first and second axial directions respectively. It will be appreciated that the first and second axial directions are the opposite directions parallel to the turbocharger axis 5a.

Each pin 69 protrudes radially outwardly from the respective bore 43 in the carrier member 39 and passes through a respective said slot 50 in the cam member 47. The pin 69 passes radially outwardly of the slot 50 into a respective said axial slot 55 in the annular flange 52 of the wall member 53 of the bearing housing 4. Each pin 69 is slidable axially within the respective axial slot 55. However, the slot 55 is sized to substantially prevent rotation of the pin 69 about the turbocharger axis 5a. In this respect, the slot 55 is of a width, in the circumferential direction, that is substantially the same as that of the pin 69 such that the slot 55 prevents the rotation of the pin 69 about the turbocharger axis 5a. Accordingly, due to the engagement of the pins 69 within the radial bores 43 in the carrier member 39, the carrier member 39 is rotationally fixed relative to the bearing housing 4, about the turbocharger axis 5a.

The method of operation of the actuation mechanism will now be described. In order to move the shroud 1 1 axially, so as to vary the width of the annular inlet passageway 10, the cam member 47 is rotated about the turbocharger axis 5a. This causes movement of each slot 50 relative to the respective pin 69 that passes through the slot 50. Each inner surface 51 of the cam member 47 that defines a respective slot 50 engages the pin 69 received within the slot 50 and acts to move the pin 69 in the axial direction. Due to the engagement of each pin 69 with the inner surface 56 of the annular flange 52 that defines the respective axial slot 55, the pin 69 is prevented from rotating. The reaction force exerted by this inner surface 56 on the pin 69, in combination with the force exerted on the pin by the rotating inner surface 51 that defines the respective slot 50, causes each pin 69 to move axially along the respective slot 56, in the inboard direction.

Due to the engagement of each pin 69 within the radial bores 43 in the carrier member 39, this causes the carrier member 39, and therefore the shroud 1 1 (which is fixed to the carrier member 39) to move in the axial direction. In this regard, the carrier member 39 slides axially on the support member 32. The support member 32 is made of stainless steel, coated with a low friction material so as to facilitate the movement of the carrier member 39 over the support member 32. The coating material is also wear resistant so as to prevent wear of the support member 32 due to the movement of the carrier member 39 over it. In the described embodiment the coating is CM1 1 or the support member is subject to a boronised heat treatment.

Rotation of the cam member 47 in the anti-clockwise direction (when viewed looking from the turbine end in Figure 2), acts to move the inboard surface 12 of the radial wall 18 of the shroud 1 1 towards the facing inboard surface 17 of the turbine housing 2. Rotation of the cam member 47 in the clockwise direction acts to move the inboard surface 12 of the radial wall 18 of the shroud 1 1 away from the facing inboard surface 17 of the turbine housing 2. The actuation mechanism further comprises a rotatable arm assembly 57 mounted to the bearing housing 4 (the rotatable arm assembly 57 is shown in more detail in figures 22 and 23).

The rotatable arm assembly 57 comprises an elongate arm 60 that extends along a longitudinal axis and is pivotally mounted to the axially inboard surface 54 of the axially inboard wall member 53 of the bearing housing 4. A first end of the arm 60 is provided with an aperture 71 within which is received a first end of an elongate pin 59. The pin 59 extends along a longitudinal axis and passes through a generally cylindrical collar 61 which is received within a bore 62 in the axially inboard wall member 53. The collar 61 is rotationally fixed within the bore 62 by virtue of an interference fit.

The pin 59 is rotatable within the collar 61 . The arm 60 is rotatably fixed to the pin 59 so as to rotate with the pin 59. In this respect, the pin 59 forms an interference fit within the aperture 71 in the first end of the arm 60.

A second end of the arm 60 is provided with an axially extending protrusion 58. The protrusion 58 is generally cylindrical, having a substantially circular cross-section about a longitudinal axis of the protrusion 58. The longitudinal axis of the protrusion 58 is substantially perpendicular to the longitudinal axis of the arm 60. A second end of the pin 59 is received within an aperture in an actuator arm 63. The second end of the pin 59 forms an interference fit with the aperture such that the pin 59 rotates with the actuator arm 63.

The actuator arm 63 is disposed on an axially outboard side of the wall member 53 and is connected to a pneumatic actuator (not shown). The actuator is arranged to rotate the actuator arm 63 so as to rotate the pin 59 about its longitudinal axis, which rotates the arm 60 about the longitudinal axis of the pin 59. The arm 60 and protrusion 58 are mounted within a recess 400 in the flange 53 of the bearing housing, for rotation within said recess 400. The recess 400 extends from the axially inboard surface of said flange 53, in the axially outboard direction and extends in the circumferential direction.

The recess 144 in the carrier member 39 that is proximal to the rotatable arm assembly 57 provides a clearance for the arm 60 to rotate. In addition, the circumferentially extending gap 152 in the annular flange 52 so allows clearance for the arm 60 to rotate. The cam member 47 is provided with a radially extending protrusion 66 which protrudes radially outwardly from the radially outer surface 48 of the cam member 47 (see Figure 5). The protrusion 66 has an inner surface 67 which defines a cavity 68. The cavity 58 is sized and dimensioned to receive the axially extending protrusion 58 of the arm 60.

The protrusion 58 of the arm 60 is received within the cavity 68 such that it is rotationally fixed relative to the radial protrusion 66. Accordingly, the rotation of the arm 60 rotates the protrusion 58, which, by virtue of its engagement within the cavity 68, rotates the cam member 47 about the turbocharger axis 5a. The arm 60 is rotatable in either direction so as to rotate the cam member 47 in either rotational direction about the turbocharger axis 5a. This rotation of the cam member 47 acts to move the shroud 1 1 in either axial direction so as to vary the width of the annular inlet passageway 10, as described above.

The variable geometry turbine 91 (including the cam member 47, the pins 69, the carrier member 39, the support member 32, the shroud 1 1 and the nozzle ring 13) and the annular axially extending flange 52 provided with said axial slots 55 together form a turbine assembly.

The cam member 47, the pins 69, the carrier member 39, the support member 32, the shroud 1 1 and the nozzle ring 13, together form a cartridge assembly 1400. The cartridge assembly 1400 is easy to install and remove from the turbocharger 1 since it may be installed and removed as a single piece. In this regard, in order to install the cartridge assembly, the cartridge assembly is mounted in position on the bearing housing 4 and the turbine housing 2 is then attached to the bearing housing 4 so as to sandwich the cartridge assembly within the cavity 24, between the bearing housing 4 and the turbine housing 2.

In order to facilitate the correct orientation of the cartridge assembly 1400, the nozzle ring 13 is provided with a protrusion 124 (see Figure 8) that extends axially outboard from the outboard surface 26 of the nozzle ring 13. The protrusion 124 is generally elongate and has a generally semi-circular cross-sectional shape. The radially outer surface 27 of the inboard portion 1 10 of the bearing housing 4 is provided with a radially inwardly and axially outboard extending recess 64 defined by an inner surface 65. The recess 64 has a generally semi-circular cross-sectional shape. The recess 64 is arranged to receive the protrusion 124 on outboard surface 26 of the nozzle ring 13. When the protrusion 124 is received within the recess 64, the nozzle ring 13 is automatically aligned in its correct rotational orientation. Accordingly, the engagement of the protrusion 124 and the recess 64 facilitates the correct rotational orientation of the nozzle ring, and therefore of the entire cartridge assembly 1400. The variable geometry turbine assembly of the invention provides for a relatively compact variable geometry turbine 91 that is particularly suited for use on small variable geometry turbochargers. In addition, since it only requires a relatively small cavity to house the actuation mechanism, this reduces the pressure differential experienced during filling and scavenging of the exhaust gas in the housing. In addition, since it does not require the yoke and push rods of prior-art designs, it has improved sealing and does not require water cooling.

Furthermore, the cartridge assembly may be easily and conveniently retro fitted to existing turbines so as to convert them into variable geometry turbines. In this regard, the bearing housing 4 of an existing turbine may be provided with said axial slots 55 and said cartridge assembly 1400 mounted in a cavity between the bearing housing and turbine housing, to convert it into a variable geometry turbine.

Referring to Figures 25 to 46 there is shown a variable geometry turbocharger comprising a variable geometry turbine assembly according to a second embodiment of the present invention. The variable geometry turbocharger of the second embodiment is identical to the variable geometry turbocharger 1 of the first embodiment, except for the differences described below. Corresponding features are given corresponding reference numerals. The turbocharger of the second embodiment differs from that of the first embodiment in that the axially extending slots 55 in the annular axially extending flange 52 of the bearing housing 4 are located radially outwardly of their position in the first embodiment. Furthermore, the support member 32 is sealed against the bearing housing 4 in a reciprocal manner to the first embodiment. In this regard, the annular flange 35, provided on the radially inner surface 34 of the support member 32 is provided, substantially midway along its length in the axial direction, with an annular groove 300 (see Figure 34). The annular groove 300 extends radially inwardly from the radially inner surface of the annular flange 35 and extends, in the circumferential direction, about the turbocharger axis 5A, substantially about the inner circumference of the support member 32. An annular ring seal 301 (see Figure 25) is received within the groove 300 and seals the support member 32 against the radially outer surface 27 of the bearing housing 4. In this regard, the annular groove 300 and seal 301 replaces the annular groove 36 in the bearing housing and the annular seal 37 of the first embodiment so as to provide an alternative sealing arrangement to seal the support member 32 against the radially outer surface 27 of the bearing housing 4. The second embodiment of the turbocharger also differs from the first embodiment in how the cam member 47 is coupled to the movable shroud 1 1 . In this regard, the axially extending annular flange 19 of the shroud 1 1 is provided, towards its inboard end, with a plurality of circumferentially distributed radial bores 302. Each bore 302 extends from the radially outer surface 22 of the axially extending flange 19 to a radially inner surface 303 of the axially extending flange 19 (see Figure 36). Each bore 302 extends from the radially outer surface 22 to the radially inner surface 303 along a longitudinal axis that is substantially parallel to the radial direction. Each bore 302 has a substantially circular cross-sectional shape (about its longitudinal axis). Each bore 302 is for receiving a respective said pin 69 (as described in more detail below).

In this embodiment, the carrier member 39 and the shroud 1 1 are not connected to each other by the stepped arrangement 23 of the first embodiment. In this regard, the axially extending flange 19 of the shroud 1 1 is of substantially uniform thickness across its length in the axial direction and so is not provided with said section 23 that defines a step.

Instead, the axial flange 19 of the shroud 1 1 extends inboard substantially across the axial length of the carrier member 39. In this regard, respective axially inboard ends of the axial flange 19 of the shroud 1 1 and of the radially outer surface 41 of the carrier member 39 are substantially axially aligned. The radially outer surface 41 of the carrier member 39 forms an interference fit with the adjacent radially inner surface 303 of the axially extending flange 19 of the shroud 1 1.

The radial bores 43 in the annular wall 1 17 of the carrier member 39 are substantially aligned in, the circumferential direction, with the respective bores 302 in the annular flange 19 of the shroud 1 1 . In addition, the slots 50 in the cam member 47 overlap the radial bores 302, 43, in the axially extending flange 19 of the shroud 1 1 and in the carrier member 39. As with the first embodiment, each pin 69 is received within a respective radial bore 43 in the carrier member 39. In addition, in this embodiment, each pin 69 passes through a respective said bore 302 in the axial flange 19 of the shroud 1 1 . In this way, the shroud 11 is coupled to the carrier member 39 due to said interference fit and due to the pins 69 engaging in the bores 302 in the axial flange 19 of the shroud 1 1 . In this respect, each bore 302 in the flange 19 has a diameter that is substantially the same (or slightly greater than) the diameter of the pins 69 so that as the pin 69 move in the axial direction, the shroud 1 1 is also moved in the axial direction (i.e. the shroud 1 1 is axially fixed relative to the pins 69). The method of operation of the actuation mechanism is substantially the same as that for the first embodiment. In this respect, the rotation of the cam member 47 causes movement of each slot 50 relative to the respective pin 69 that passes through the slot 50. The inner surfaces 51 of the cam member 47, that define the slots 50, engage the pins 69 so as to move them in the axial direction. The engagement of each pin 69 with the inner surface 56 of the annular flange 52 that defines the respective axial slot 55 in the bearing housing 4 prevents the pin 69 from rotating and guides the pin 69 in the axial direction. The engagement of the pin 69 in the radial bores 43 in the carrier member 39 causes the carrier member 39 (and therefore the shroud 1 1 ) to move in the axial direction), with the seal 44 in the annular groove 46 in the carrier member 39 sliding across the radially outer surface of the support member 32. In addition, the engagement of the pins 69 in the radial bores 303 in the shroud 1 1 also acts to move the shroud 1 1 in the axial direction, so as to vary the width of the inlet passageway.

However, in this embodiment, the helical slots 50 are oriented in the opposite rotational sense. Accordingly, rotation of the cam member 47 in the clockwise direction (when viewed looking from the turbine end of Figure 26), acts to move the inboard surface 12 of the radial wall 18 of the shroud 1 1 towards the facing inboard surface 17 of the turbine housing 2. In this embodiment, the radially extending protrusion 66 of the cam member 47 has been replaced with a slot 304. The slot 304 extends radially inwardly, from the radially outer surface 48 of the annular wall 104 of the cam member 47, to the radially inner surface 49, along a longitudinal axis. The longitudinal axis is substantially parallel to the radial direction. The slot 304 has a substantially rectangular cross-sectional shape (with an open outboard side), about its longitudinal axis.

The slot 304 extends in the inboard axial direction from an axially outboard surface of the annular wall 104 of the cam member 47 and terminates within the axial thickness of said annular wall 104 such that the slot 304 is open at its axially outboard end and is closed at its axially inboard end.

The axially extending protrusion 58 of the arm 60 is of a complimentary shape to that of the slot 304 in the cam member 47. In this regard, the protrusion 58 has a curved rectangular cross-sectional shape that forms an interference fit with the slot 304 such that rotation of the protrusion 58 about the turbocharger axis, rotates the cam member 47 about the turbocharger axis.

The removal of the radially extending protrusion 66 of the cam member 47 of the first embodiment advantageously reduces the weight of the actuation mechanism.

As shown in Figure 37, an outboard end of the axially extending flange 19 of the shroud 1 1 is provided with a slot 305 (see Figure 37). The slot extends axially inboard from the outboard end of the flange 19 and extends in the circumferential direction, part way along the circumference of the flange 19. The slot is adjacent to the arm 60 of the rotatable arm assembly 57 and provides clearance for the arm 60 to rotate.

Referring to Figures 47 to 70 there is shown a variable geometry turbocharger comprising a variable geometry turbine assembly according to a third embodiment of the present invention. The variable geometry turbocharger of the third embodiment is identical to the variable geometry turbocharger of the second embodiment, except for the differences described below. Corresponding features are given corresponding reference numerals. The turbocharger of the third embodiment differs from that of the second embodiment in that the annular flange 52 is not provided with said axially extending slots 55. Instead, the vanes 15 of the nozzle ring 13 and the slots 16 in the shroud 1 1 are arranged such that the engagement of the vanes 15 within the slots 16 substantially prevents the shroud 1 1 , and carrier member 39, from rotating, as the pins 69 are urged in both the axial and circumferential directions due to the rotation of the cam member 47. In this regard, the slots 16 have a complimentary shape to the vanes 15. In a similar manner to the second embodiment, rotation of the cam member 47 in the clockwise direction (when viewed looking from the turbine end of Figure 48), acts to move the inboard surface 12 of the radial wall 18 of the shroud 1 1 towards the facing inboard surface 17 of the turbine housing 2.

In this embodiment, there are no said axial guide slots 55 provided in said bearing housing. Accordingly, as the cam member 47 rotates, the pins 69 are not prevented from rotating by said axial guide slots 55.

In this regard, the rotation of the cam member 47 (in the clockwise direction) causes the inner surfaces 51 of the cam member that define the slots 50 to engage the respective pins 69 such that the pins 69 are urged in the clockwise rotational direction about the turbine axis. This acts to rotate the carrier member, and therefore the shroud 1 1 about the turbine axis (in said clockwise direction). However, the engagement of the vanes 15 within the slots 16 acts to limit the rotation of the shroud 1 1 and to guide the shroud 1 1 in the axial direction. In this regard, as the shroud 1 1 moves axially, the slots 16 slide over the vanes 15.

Due to the rotational force exerted on the shroud 1 1 by the cam member 47, via the pins 69, the shroud 1 1 is rotated by a small amount such that, for each slot 16, a radially outer section of a surface of the shroud that defines the slot abuts a radially outer surface the vane 15 received within the slot. This substantially closes the high pressure side of the slot and substantially prevents exhaust gas on this side from passing from the inlet passageway through the slots 16.

Alternatively, the actuation mechanism may be arranged such that rotation of the cam member 47 in the anti-clockwise direction (when viewed looking from the turbine end of Figure 48), acts to move the inboard surface 12 of the radial wall 18 of the shroud 1 1 towards the facing inboard surface 17 of the turbine housing 2. In order to do this, the rotational orientation of the helical slots may be reversed.

In this case, the rotation of the cam member 47 (in the anti-clockwise direction) causes the inner surfaces 51 of the cam member that define the slots 50 to engage the respective pins 69 such that the pins 69 are urged in the anti-clockwise direction about the turbine axis. This acts to rotate the carrier member 39, and therefore the shroud 1 1 about the turbine axis (in said anti-clockwise direction). However, the engagement of the vanes 15 within the slots 16 acts to limit the rotation of the shroud 1 1 and to guide the shroud 1 1 in the axial direction.

Due to the rotational force exerted on the shroud 1 1 by the cam member 47, via the pins 69, the shroud 1 1 is rotated by a small amount such that, for each slot 16, a radially inner section of a surface of the shroud that defines the slot abuts a radially inner surface the vane 15 received within the slot. This substantially closes the low pressure side of the slot and substantially prevents exhaust gas on this side from passing from the inlet passageway through the slots 16.

Accordingly, in this way, the actuation mechanism may be arranged in either rotational sense to provide desired performance characteristics.

Furthermore, in this embodiment, the pins 69 are integrally formed with the carrier member 39. In this regard, the pins 69 form part of the carrier member 39 and protrude radially outwardly from a radially outer surface of the carrier member 39. As with the preceding embodiments, the pins 69 each extend from a radially inner end to a radially outer end along a longitudinal axis that is substantially parallel to the radial direction. In this embodiment, each pin 69 has a cross-sectional shape, about its longitudinal axis, that is of a generally square shape with curved corners. This shape advantageously increases the contact area between the pins 69 and the surfaces 51 that define the slots 50, which reduces the contact stresses between the pins 69 and said surfaces 51 .

In addition, since the pins 69 are integral with the carrier member 39 this facilitates assembly of a cartridge assembly 1400, formed by the cam member 47, the pins 69, the carrier member 39, the support member 32, the shroud 1 1 and the nozzle ring 13, since this provides few separate components to have to bring together. In this embodiment, the cam member 47 is of a thinner radial thickness compared to that of the previous embodiments, but is provided with a plurality of lugs 320 circumferential distributed about the cam member 47 (see figure 48). The lugs 320 are of greater thickness (in the radial direction) than the remaining sections of the cam member 47 provided between the lugs 320. In this embodiment, the cam member 47 is provided with three of said lugs 320, distributed in the circumferential direction.

Each lug 320 has an inner surface 51 that defines a respective said helical slot 50 for receiving a respective said pin 69. An outboard end of each helical slot 50 is open, so as to allow insertion of a respective said pin 69 (which is integral with the carrier member 39) through the open end and into the slot 50.

Providing the lugs 320 of increased thickness advantageously increases the contact area between the pins 69 and the inner surfaces 51 of the lugs 320, that define the helical slots 15. This advantageously reduces the contact stresses between the pins 69 and the inner surfaces 51 that define the helical slots 15. In addition, since the sections of the cam member 47 between the lugs 69 are of reduced thickness compared to the lugs 320, this reduces the overall weight of the cam member 47 (and therefore of the turbocharger), than if said sections of the cam member 47 were of the same thickness as the lugs 320.

Alternatively, instead of having pins 69 that are integral to the carrier member 39, the pins 69 may be separate entities to the carrier member 39 and may be receivable within bores 43 in the carrier member 39, as in the preceding embodiments.

In this embodiment, the carrier member 39 is attached to the shroud 1 1 as in the first embodiment, i.e. the axially extending flange 19 of the shroud 1 1 has a section 23 (see Figure 60) towards its outboard end that is of reduced thickness. A radially inner surface of the inboard section 42 of the annular wall 1 17 of the carrier member 39 is welded to a radially outer surface of the outboard section of reduced thickness 23 of the axial flange 19 of the shroud 1 1 . It will be appreciated that carrier member 39 may be fixedly attached to the shroud 1 1 by any suitable means, including brazing. In this embodiment, the nozzle ring 13 is provided with a protrusion 124 for rotatably orienting the nozzle ring 13 relative to the support member 32 (see Figure 54). The protrusion 124 is substantially cylindrical and extends axially outboard, from the outboard surface 14 of the annular wall 25 of the nozzle ring 13. A radially inner surface of the annular wall member 131 of the support member 32 is provided with a recess 315 for receipt of the protrusion 124 of the nozzle ring 13. The recess 315 extends axially inboard from an inboard end of said wall member 131 . The recess 315 has a complementary shape to that of the protrusion 124. Similarly, the annular wall member 131 of the support member 32 is provided with a cylindrical bore 316 that extends axially inboard from the axially outboard surface of the annular wall member 131 .

An axially inboard surface of the bearing housing 4 is provided with a bore 318 that extends in the axially outboard direction. The bore 318 is for receipt of a locating pin 317 (see Figure 58) that is also received within the bore 316 in the support member 32.

In this embodiment the seal 27, 301 of the preceding embodiments, that sealed the radially inner surface of the support member 32 to the radially outer surface of the bearing housing 4 is not present and the radially inner surface of the support member 32 forms a press fit engagement with the radially outer surface of the bearing housing 4.

When the pin 317 is received within the bore 318 in the bearing housing and in the bore 316 in the support member 32, the support member 32 is oriented correctly relative to the bearing housing 4. In addition, when the protrusion 124 of the nozzle ring 13 is received within the recess 315 in the support member 32, the nozzle ring 13 is oriented correctly relative to the support member 32. Accordingly, said protrusion 124, recess 315, bore 316, pin 317 and bore 318 provide a means of correctly orienting (in the circumferential direction) both the support member 39 and the nozzle ring 13 (and therefore the shroud 1 1 ) relative to the bearing housing 4, during assembly. This facilitates ease of assembly of the cartridge assembly 1400. In this embodiment, the rotatable arm assembly 57 (see figures 69 and 70) is substantially the same as in the preceding embodiments, except in that the protrusion 58 has a substantially square cross-sectional shape, with rounded corners. The slot 304 in the cam member 47 is a complementary square shape to the protrusion 58.

In this embodiment, the heat shield 31 is no longer integral with the nozzle ring 13, but is a separate entity. The nozzle ring 31 is mounted on a radially outer surface of the heat shield 31 , between the radially outer surface of the heat shield 31 and axially adjacent radially inner surfaces of the support member 32 and shroud 1 1.

An axially outboard end of a radially outer annular axially extending flange of the heat shield 31 is provided with an annular, radially outwardly extending, lip 330. The lip 330 is disposed axially outboard of the tolerance ring 38, and is sandwiched between the tolerance ring 38 and a contacting axially inboard surface of the support member 32.

An inboard side of the tolerance ring 38 contacts an inboard surface of the nozzle ring 13, which biases the vanes 15 of the nozzle ring 13 against the facing surface 17 of the turbine housing. Accordingly, in this embodiment, the tolerance ring 38 directly contacts the nozzle ring 13 to bias it in the axially inboard direction. The heat shield 31 is separate to the nozzle ring 13 and is mounted to the bearing housing 4 such that its lip 330 is disposed axially outboard of the tolerance ring 38. Accordingly, the tolerance ring 38 does not exert a force on the heat shield 31 in the axially inboard direction (as in the previous embodiments). This is advantageous in that, during assembly, the heat shield 31 is not urged in the axially inboard direction (which would otherwise occur before the turbine housing is attached to the bearing housing 4). Therefore the heat shield 301 does not exert a force, in the inboard direction, on the turbine wheel 6, which would be undesirable.

The axially extending flange 52 of the bearing housing 4 is provided with three of said circumferentially extending gaps 152, equally spaced in the circumferential direction. This reduces the weight of the bearing housing 4. The method of operation of the actuation mechanism is substantially the same as that for the preceding embodiment.

Referring to Figures 71 to 95 there is shown a turbocharger comprising a variable geometry turbine assembly according to a fourth embodiment of the present invention. The variable geometry turbocharger of the fourth embodiment is identical to the variable geometry turbocharger of the third embodiment, except for the differences described below. Corresponding features are given corresponding reference numerals.

The turbocharger of the fourth embodiment differs from that of the third embodiment in that the shroud 1 1 is formed from a radially outer, axially extending annular flange 501 , a radially inner axially extending annular flange 503 and a radially extending annular wall 502 that connects inboard ends of the radially outer and inner axially extending flanges 501 , 503.

An inboard radial surface of the radially extending annular wall 502 forms said inboard surface 12 that defines the inlet passageway. In this regard, the radially extending annular wall 502 forms the movable wall member and the radially outer, axially extending annular flange 501 forms the carrier member. Accordingly, in this embodiment the shroud 1 1 comprises the movable wall member and the carrier member. As with the preceding embodiments, the inboard surface 12 is provided with said plurality of slots 16 for receipt of the nozzle vanes 15. The radially outer, axially extending flange 501 extends outboard from a radially outer end of the annular wall 502. An inboard end of the axially extending flange 501 is welded to said radially outer end of the annular wall 502.

In this embodiment, the pins 69 are integrally formed with the radially outer axially extending flange 501 , towards an outboard end of said flange 501. The pins 69 extend radially outwardly from a radially outer surface 518 of said flange 501 .

The radially inner axially extending flange 503 has a radially inner surface 514 that is mounted on a radially outer surface of the heat shield 31 . The nozzle ring 13 is mounted within the shroud 1 1 . In this regard, the nozzle ring 13 comprises a radially extending wall 504, where the vanes 15 extend axially inboard from an inboard surface 14 of the wall 504 (see Figure 74). The radially extending wall 504 is provided with a radially outer and inner annular grooves 505, 506 that each house an annular seal 507, 508. The seals 507, 508 respectively seal the radial wall 504 of the nozzle ring 13 against a radially inner surface of the radially outer axially flange 501 and against a radially outer surface of the radially inner axially extending flange 503, as the shroud 1 1 moves axially, relative to the nozzle ring 13. The seals 507, 508 advantageously prevent exhaust gas, that has passed through the slots 16, from passing outboard of the seals 507, 508. Furthermore, the radially inner seal 508 prevents this exhaust gas from passing to the turbine wheel.

The method of operation of the actuation mechanism is substantially the same as that for the preceding embodiment. In each of the described embodiments, the nozzle ring 13 and shroud 1 1 are mounted on the same axial side of the inlet passageway. In combination with the actuation mechanism of the above described embodiments, this advantageously produces a compact arrangement and allows the actuation mechanism to be formed as a cartridge.

In each of the described embodiments, the carrier member 39 is annular and the cam member 47 and the carrier member 39 axially overlap for at least one axial position of the shroud 1 1 . In combination with the actuation mechanism of the above described embodiments, this advantageously produces a compact arrangement and allows the actuation mechanism to be formed as a cartridge.

It will be appreciated that the cam member 47 and the carrier member 39 axially overlap for a plurality of axial positions of the shroud 1 1 .

In each of the described embodiments, the cam member 47 is disposed radially outwardly of the shroud 1 1 . In combination with the actuation mechanism of the above described embodiments, this advantageously produces a compact arrangement and allows the actuation mechanism to be formed as a cartridge. It will be appreciated that numerous modifications to the above described variable geometry turbine assembly may be made without departing from the scope of the invention as defined by the claims. In this regard, in the described embodiments the slots 50 in the cam member 47 each form a formation and the pins 69 each form a co-operating formation that is coupled to the carrier member 39 such that as the co-operating formation is moved in the axial direction, the carrier member 39 is moved in the axial direction. In an alternative arrangement to that described, the slots 50 may be provided in the carrier member 39, with the cam member 47 provided with said pins 69 such that rotation of the cam member 47 relative to the carrier member moves the carrier member 39 in the axial direction.

It will be appreciated that the invention is not limited to the use of said pins 69 and slots 50. The pins 69 may be any radially extending formation and the slots 50 may be any complimentary recess for receiving the radially extending formation.

In the described embodiments the slots 50 extend in both the circumferential direction and the axial direction and the pins 69 are arranged to move along the slots 50. Alternatively, or additionally, the pins 69 (or any radially extending formation) may extend in both the circumferential direction and the axial direction (e.g. having a helical shape), with the slots 50 being for receipt of the pins 69 such that rotation of the cam member 47 moves the carrier member 39 in the axial direction.

The features of any of the described embodiments may be combined with the features of any of the other described embodiments. For example, in any embodiment, the pins 69 may be coupled to the shroud 1 1 as in any other embodiment. For example, in the fourth embodiment the pins 69 are part of the shroud 1 1 . However, the pins 69 may not be part of the shroud and may instead be received within bores in the shroud and/or carrier member 39 as in the first to third embodiments. The different shapes of the slots 50 in the cam member 47 that are shown in Figures 24a to 24c may be used for any of the described embodiments.

In the described embodiments the shroud 1 1 is axially movable and the nozzle ring 13 is axially fixed, relative to the bearing housing 4. Alternatively, the nozzle 13 may be axially movable and the shroud 1 1 fixed in the axial direction. In this case, the nozzle ring 13 is attached to the carrier member 39, instead of the shroud 16 such that the actuation mechanism moves the nozzle ring 13. In this case, the nozzle ring 13 and shroud 13 may be mounted on opposite axial sides of the inlet passageway. Both the shroud 13 and the nozzle ring 13 may be movable in the axial direction.

In the described embodiments the actuation mechanism is disposed within a cavity 24 between the bearing housing 4 and the turbine housing 2, on the side of the bearing housing 4. Alternatively, the actuation mechanism may be provided in a cavity on the turbine housing 2 side of the annular inlet passageway 10. The actuation mechanism may be housed in any suitable location.

The second to the fourth embodiments may have features of the first embodiment of the annular axially extending flange 52 of the bearing housing 4 provided with said axially extending slots 55, with the pins 69 received within said slots 55. In the described embodiments the carrier member 39 is disposed radially inwardly of the cam member 47. Alternatively, the carrier member 39 may be disposed radially outwardly of the cam member 47. In this case, the carrier member 39 may be attached to the shroud 1 1 by any suitable arrangement, for example via a flange which extends in the axial direction and the radially inwardly direction so as to pass over and around the cam member 47 to the shroud 1 1 .

Additionally, or alternatively, the axially extending flange 19 of the shroud may be mounted radially outwardly of the cam member 47.

In the described embodiments the cam member 47 is provided with a set of three slots 50. Alternatively, the cam member 47 may be provided with only a single slot 50. The cam member 47 may be provided with one or more said slots 50.

In this regard, the carrier member 39 may be provided with a corresponding number of said radial bores 43. In relation to the first embodiment the annular axially extending flange 52 of the bearing housing 4 may be provided with a corresponding number of said axially extending slots 55 and with a corresponding number of said radial pins 69 protruding through the respective slots/bores.

In the first embodiment the axial slots 55 are provided in the annular axially extending flange 52 of the bearing housing 54. Alternatively, the slots 55 may be provided in a different housing of the turbocharger 1.

The rotatable arm assembly 57 may be mounted to any housing of the turbocharger 1 . In the described embodiments the nozzle ring 13 is provided with a plurality of inlet vanes 15 and the shroud 1 1 is provided with a plurality of slots 16. Alternatively, the nozzle ring may not be provided with said inlet vanes 15. In this case, the shroud 1 1 may not be provided with said slots 16. The described variable geometry turbine assembly is described when used as part of a variable geometry turbocharger 1. However, it will be appreciated that the variable geometry turbine assembly may be used as part of any turbomachine and is not limited to use with turbochargers. For example, the variable geometry turbine assembly of the invention may be used as part of a power turbine, or any other turbomachine. In the described embodiments the carrier member is coupled to the shroud, so that axial movement of the carrier member causes axial movement of the shroud, by being directly attached to the shroud. Alternatively, the carrier member may be so coupled to the shroud by being indirectly connected to the shroud, for example via an intermediary coupling member. The same applies to the coupling of the carrier member to the nozzle ring, where the nozzle ring comprises the movable wall member.

The variable geometry turbine assembly may not comprise the support member 32. In this case, the carrier member 39 may be axially slidably mounted on a housing of the variable geometry turbine assembly, such as the bearing housing 4.

In the described embodiment the nozzle ring is provided with said protrusion 124 for receipt in said recess 64. Alternatively, or additionally, the cam member and/or the support member may be provided with said protrusion. The bearing housing may be cast around the support member 32. In order to do this, the support member 32 would be placed into a casing mould and molten metal poured around it. The support member 32 would then be machined in conjunction with the bearing housing to help reduce tolerance stack-ups. The annular groove 36 and seal 37 may then be omitted as there is no longer a potential leakage path needing to be sealed.

The facing inboard surface 17 of the turbine housing 2 may also be movable in the axial direction so as to vary the width of the inlet passageway.