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WO/2020/178510A1 |
The invention relates to a method for assembling a body (71) and a cover (72) of a vane (7) by polymerisation of a resin. The cover (72) is positioned on a junction face of the body (71) covered with this resin. According to the inventio...
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WO/2020/175533A1 |
A turbine blade (21) has a ventral surface (21P) that extends in the radial direction, which intersects a vapor flow direction, and faces the upstream side of the flow direction. A slit (5) is formed on the downstream side in the ventral...
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WO/2020/174753A1 |
This member for rotary machines comprises an annular member body (A) extending along the circumferential direction about an axial line (Am). The annular member body A includes base plates which are made of a first material and which are ...
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WO/2020/174801A1 |
This diaphragm for a steam turbine has a diaphragm inner wheel, a diaphragm outer wheel, and a wing section that are integrally formed, wherein: the diaphragm comprises a collector ring that holds a seal fin having a radial spill strip s...
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WO/2020/175192A1 |
A turbine blade (21) has a ventral surface (21P) that extends in the radial direction, which intersects with a vapor flow direction, and faces the upstream side of the flow direction. A slit (5) is formed on the downstream side in the ve...
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WO/2020/174163A1 |
The invention relates to a method of assembling a member (71) and a cap (72) of a vane (7) using a tool (9) which allows the application of a pressing force of the cap (72) against the member (71) during a step of polymerisation by heati...
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WO/2020/171813A1 |
A nozzle ring (10) for a radial turbine is described. The nozzle ring includes a disc-shaped main body (11) having a central opening (12) for passing a shaft there through. Additionally, the nozzle ring includes guide vanes (14) disposed...
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WO/2020/170903A1 |
A turbine rotor fixing device that enables fixing the radial direction and the axial direction of a turbine rotor with ease, and a turbine module transport method are provided. This fixing device (30) of a turbine rotor (11) is provided ...
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WO/2020/170673A1 |
A passenger compartment (1) comprises: a passenger compartment body (1B), which covers a rotor (21) of a steam turbine (100) from the outer side, and in which is formed an exhaust port (E) through which steam is horizontally exhausted; a...
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WO/2020/128038A9 |
A gas turbine engine comprising at least one radially extending bleed passage in fluid communication with at least one generally circumferentially extending plenum. A plenum has an upstream end in fluid communication with a bleed passage...
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WO/2020/172493A1 |
In an aspect, a method of filling a plurality of cooling holes (12) in an airfoil component (10), the method comprises injecting a curable composition into a fill channel (8) such that the curable composition flows through the fill chann...
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WO/2020/170376A1 |
A turbocharger equipped with: a rolling bearing that includes at least one rolling body and that rotatably supports a rotary shaft; a bearing support cylinder that is positioned on the outside of the rolling bearing in the radial directi...
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WO/2020/165527A1 |
The invention relates to a turbomachine blade (54) comprising a body (60) that extends mainly in a plane defined by a main axis B and a longitudinal direction, which is defined by a lower surface wall (66), an upper surface wall (68), a ...
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WO/2020/167889A1 |
Provided is a method of aligning a gas turbine shaft. The method includes securing a laser sensor to a first shaft of a first rotary component axially connected to a rotor of a gas turbine, and securing a laser generating device to a sec...
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WO/2020/167598A1 |
A turbine blade has an attachment root and an airfoil. A cooling passageway system has a plurality of trunks extending from respective inlets along the root inner diameter end from a leading trunk near a first axial end to a trailing tru...
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WO/2020/167315A1 |
A masking system (105) for a turbine including a first quantity of blades (35) attached to a rotor (30) and arranged adjacent one another to define a blade (35) row with each blade (35) including a blade root (70), includes a second quan...
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WO/2020/161437A1 |
The invention relates to a method for monitoring the state of health of at least two vibration sensors of a twin-spool turbomachine comprising a low-pressure spool and a high-pressure spool, one vibration sensor being located at the fron...
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WO/2020/160963A1 |
A shaft seal system (10) of a shaft (11) supported in a bearing housing (30) of a turbomachine is described. The shaft seal system includes a rotor-side seal (19) arranged between the bearing housing (30) and the shaft (11). Additionally...
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WO/2020/157405A1 |
A turbomachine stator sector (100) comprises a plurality of vanes (110) extending in a radial direction (DR) between a first end (110a) and a second end (110b) and in an axial direction (DA) between a leading edge (111) and a trailing ed...
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WO/2020/157438A1 |
The invention concerns a fan casing (10) for an aircraft turbomachine, comprising an annular body (11) extending around an axis and equipped with an annular attachment flange (12a, 12b) at each of its axial ends, and an annular coating (...
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WO/2020/157432A1 |
A method for controlling the bending deformation of a shaft (14C) of a turbomachine (10) at rest subjected to the residual heat of operation of the turbomachine, in which the shaft (14C) is rotated at a speed of rotation between 0.1 and ...
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WO/2020/158072A1 |
A monitoring system that is for monitoring steam-using equipment 2. The monitoring system comprises: a trap temperature sensor that detects the temperature of a steam trap 23a that is provided to a steam-discharging part 23 and/or a stea...
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WO/2020/157409A1 |
A housing for a gas turbine fan made of composite material with a fibrous reinforcement comprising a plurality of stacked turns of a fibrous texture (100) in the form of a strip having a three-dimensional weave between a plurality of lay...
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WO/2020/157418A1 |
The invention relates to an aircraft turbomachine casing (10) having: a substantially cylindrical wall (11) extending along a longitudinal axis, an annular sound insulating shell (12) that is mounted radially inside said wall and is subs...
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WO/2020/156889A1 |
The invention relates to a protection device for protecting the rotor blades (45) of a compressor against sparks and/or particles when machining the blade tips of at least one rotor (41-43) of the compressor using a machine tool (3). Acc...
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WO/2020/158221A1 |
The present invention provides an overlay welding method with which it is possible for deformation to be adequately suppressed, even with a thin metal overlay layer or base material. More specifically, the present invention provides an o...
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WO/2020/151925A1 |
A gas (or steam) turbine (200) is disclosed including: a rotor with at least one array of rotor blades (213-1), a stator with a casing (261) and a shroud ring (250); the shroud ring (250) extends around the array of blades rotor (213-1) ...
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WO/2020/152410A1 |
A device (30) for centering and rotationally guiding a turbomachine shaft comprises: a rolling bearing outer ring (46); a bearing support (34) having a radially inner annular surface (55) surrounding the outer ring (46); a connection str...
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WO/2020/151578A1 |
A turbine housing integrated with an active clearance control apparatus comprises a housing (100), a gas inlet pipe (200), a gas collection container (300), and a shunt pipe (400). The housing (100), the gas inlet pipe (200), the gas col...
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WO/2020/148086A1 |
The invention relates to a device (1) for driving a shaft (81) of a jet engine (80) for the purpose of inspection. The device (10) comprises a drive unit (10) having a part (11) that moves in conjoint rotation with the shaft, the co-rota...
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WO/2020/148081A1 |
The invention relates to a device (1) for driving a shaft (81) of a jet engine (80) for inspection purposes. In one embodiment, the device (1) comprises a drive unit (10) having a part (11) co-rotating with the shaft, wherein the co-rota...
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WO/2020/149854A1 |
A pre-swirler (14) for a gas turbine engine (10) is presented. The pre-swirler (14) includes a hole (26) drilled through a component (11, 12) of the gas turbine engine (10). The pre-swirler (14) includes a pre-swirler plug (16) that is p...
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WO/2020/148493A1 |
The invention relates to an aerodynamic arm (100) for an aircraft turbine engine casing, characterised in that it comprises: - a tubular outer shell (110) having a generally elongate shape extending substantially along an axis (A-A), the...
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WO/2020/144435A1 |
Disclosed is a method for assembling/disassembling a turbine ring assembly comprising a turbine ring (1) made of ceramic matrix composite material and a ring support structure (3) made of metal, equipped with a central shroud (31) and at...
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WO/2020/142113A1 |
A platform seal and damper assembly for turbomachinery (100), such as fluidized catalytic cracking (FCC) expanders or gas turbine engines; and methodologies for forming such assembly are provided. An axially-extending groove (160) is arr...
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WO/2020/138307A1 |
A steam valve having a first inclined surface (61b), which is formed at the distal end portion (61A) of a valve rod (61) and in which the outer diameter of the valve rod (61) increases from the distal end toward the base end of the valve...
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WO/2020/136524A1 |
Axial turbine (100) with two supply levels for the expansion phase of a working fluid in a thermodynamic vapor cycle or in an organic Rankine cycle comprising a shaft (2), a plurality of rotor blade arrays (R1-Rn) and corresponding suppo...
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WO/2020/136374A1 |
A seal system for a bearing chamber (22) of a turbomachine includes the baffle element (70) encircling the axis (25) of the machine. The baffle element is formed with front surface including both a recess (73) which defines acircumferent...
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WO/2020/135931A1 |
A stator aerodynamic component (130, 250) is disclosed to be placed inside a flow path (500) of a working fluid of a turbomachine (1000); the component (130, 250) has one or more nozzles (135, 255) for ejecting a liquid into the flow pat...
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WO/2020/138572A1 |
The present invention relates to a turbocharger having magnetic bearings and, more specifically, to a turbocharger having magnetic bearings, which can completely remove frictional loss occurring during a rotation of a rotating shaft that...
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WO/2020/137308A1 |
An exhaust chamber (25) is equipped with: a diffuser (26) that forms a diffuser space (26s); an exhaust casing (30) that forms an exhaust space (30s) communicating with the diffuser space (26s); and an auxiliary exhaust frame (40) that f...
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WO/2020/128367A1 |
The invention concerns a part (10) for a turbomachine (1) made from composite material comprising a fibrous reinforcement (11) having a three-dimensional weave that comprises a first set of yarns (12) made from a first material, characte...
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WO/2020/128338A2 |
Turbine ring assembly having indexed flanges. The invention relates to a turbine ring assembly comprising ring segments (10) which form a turbine ring (1) and a ring support structure (3), each ring segment (10) having a part forming an ...
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WO/2020/129840A1 |
The present invention is a TiAl-based alloy containing 41–43 atomic% Al, 0–2.5 atomic% Fe, 0–2.5 atomic% Ni, 0–2.0 atomic% Mo, 0–2.0 atomic% W, 0–4.5 atomic% Cr, 0–5.5 atomic% Mn, 0–10 atomic% V, 0–10 atomic% Nb, and 0....
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WO/2020/127800A2 |
An aircraft engine circulation system comprising a conduit arranged in use to communicate a lubricant to and from one or more bearings of an engine. The conduits define a space which comprises a material that is selected to change phase ...
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WO/2020/128267A1 |
Tooling (3) for placing a propulsive assembly (2) from a horizontal position to a vertical position, comprising: - a front tool (4) comprising: • a first assembly comprising a frame (19) configured to be positioned and maintained with ...
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WO/2020/128222A1 |
A turbine ring assembly comprising ring sectors (10a, 10b) forming a turbine ring (1) and a ring support structure (3), each sector (10a, 10b) having, on a plane of section defined by an axial direction (DA) and a radial direction (DR) o...
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WO/2020/132689A1 |
There is disclosed a labyrinth seal arrangement for gas turboexpanders and the like which reduces process gas losses. The labyrinth seal includes a plurality of axially spaced seal sets with teeth facing a seal member. A plurality of ven...
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WO/2020/120863A1 |
The invention relates to a fire resistance device (50) that is designed to be placed between a mounting strut of a double-flow aircraft turbomachine and a connecting cowling with which said turbomachine is equipped, the connecting cowlin...
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WO/2020/120399A1 |
A cleaning device (10) for a turbine is described. The cleaning device (10) includes an injector main body (11) for injecting cleaning liquid into a flow channel of the turbine. The injector main body (11) includes a main flow channel (1...
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