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WO/2016/042275A1 |
The invention relates to the field of rotary blades and more particularly to a method of manufacturing a leading edge shield intended to protect such a blade. This method involves at least the steps of initial plastic deformation of at l...
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WO/2016/041799A1 |
The invention relates to a device (2, 17) for driving a stator blade (3) into a blade groove (1) which is mounted on a stator blade carrier (4) of a turbine and contains at least one caulking element (5), comprising at least one linear d...
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WO/2016/041957A1 |
The invention relates to a method for treating a composite part (10) comprising a metal protective duct (12) fixed to a core (11) by means of a binder (14), so as to be able to separate the duct from the core, comprising the steps consis...
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WO/2016/044450A1 |
A preswirler (470) for a gas turbine engine (100) diaphragm assembly (460) is disclosed herein. In embodiments, the preswirler (470) includes an outer ring (471) and an inner ring (474). The outer ring (471) includes an outer ring face (...
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WO/2016/041761A1 |
The invention relates to a turbine blade (1) having an internally cooled turbine blade airfoil (3) in which a hollow space (10) is divided by rib elements (11, 12) into at least one cooling duct (13) carrying a coolant, wherein in at lea...
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WO/2016/038280A1 |
The invention relates to a vane for a turbine engine. The vane (12') has a blade (13') and a root (18') to be inserted into an axial groove of a turbine engine disc. The upstream end (450') of the root is connected to a radially inner en...
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WO/2016/037452A1 |
Disclosed is a counter-rotation impeller mechanism, comprising at least one positive rotating shaft (1) and at least one negative rotating shaft (2), wherein the difference between the numbers of the positive rotating shaft (1) and the n...
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WO/2016/039714A1 |
A cooling system (10) positioned within a turbine airfoil (12) and having film cooling channels (16) positioned within inner and outer endwalls (18, 20) of the turbine airfoil (12), with cooling fluids supplied to the cooling channels (1...
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WO/2016/039716A1 |
An insulating system (10) for a gas turbine engine (12) configured to insulate a surface (14) to reduce thermal gradients within components (18) in the engine (12) is disclosed. The insulating system (10) may include one or more insulati...
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WO/2016/038282A1 |
The invention relates to a method (40) for repairing an upstream rail (20) of a turbine engine turbine casing (19), said casing (19) including a casing body (21) extending along a longitudinal axis, said upstream rail (20) including: a b...
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WO/2016/040367A1 |
A system and method for remanufacturing a turbocharger (100) center housing (106) include performing a machining operation on an original center housing (200) to remove a portion of a parent material from the original center housing (200...
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WO/2016/034796A1 |
The invention concerns a tubular shaft (8) of a turbomachine, comprising, at the inner periphery of same, a bath (11), substantially perpendicular to said splines (9), characterised in that said bath (11) comprises cavities (17) distribu...
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WO/2016/034487A1 |
The invention relates to a method for operating a machine plant (1) having a shaft train (2), with the steps of: a) determining, computationally, the harmonic frequency of at least one torsional vibration mode of the shaft train and dete...
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WO/2016/036367A1 |
An airfoil (10) for a gas turbine engine in which the airfoil (10) includes an internal cooling system (14) with one or more internal cavities (16) having an insert (18) contained therein that forms nearwall cooling channels (20) having ...
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WO/2016/035663A1 |
Provided are a method for manufacturing a molded ring by which it is possible to reliably and efficiently fabricate a molded ring having a reduced dead metal region. Also provided is a ring material for use in fabricating the molded ring...
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WO/2016/034822A1 |
The invention relates to a blade having a platform (14) comprising at least one bumper (40) which rises, on the inner face, from a junction to an intermediate area of the blade, located along a longitudinal axis of the blade, between the...
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WO/2016/035664A1 |
Provided is a manufacturing method for a ring formed body, the method enabling the ring formed body with a reduced dead metal region to be reliably and efficiently manufactured. In this invention, the ring formed body is manufactured in ...
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WO/2016/035618A1 |
This method for producing a powder for thermal spray is provided with: a preparation step S1 for preparing a mixed powder which contains first particles that are configured of a zirconia-based ceramic containing a first additive and seco...
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WO/2016/036366A1 |
An airfoil (10) for a gas turbine engine in which the airfoil (10) includes an internal cooling system (14) with one or more internal cavities having an insert (18) contained within an aft cooling cavity (76) to form nearwall cooling cha...
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WO/2016/035329A1 |
In the present invention, different attack angles are set for turbine blades (22) on one side and on the other side in an axial direction in accordance with a relative inflow angle of exhaust gas. In other words, a first attack angle (θ...
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WO/2016/030997A1 |
A turbocharger (1) is provided with a valve body (10) which is disposed in a suction flow path (C) leading from an inflow port (14) of a housing (4a) covering a turbine rotor blade (6) to a scroll part (15) and composed of a single piece...
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WO/2016/030614A1 |
The invention relates to a method for repairing an assembly comprising a main body (10) and an old reinforcement, the assembly comprising an initial hole passing through the old reinforcement and at least one part of the main body. The m...
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WO/2016/032506A1 |
A controlled convergence compressor flowpath (10) configured to better distribute the limited flowpath (10) within compressors (12) in turbine engines (14) is disclosed. The compressor (12) may have a flowpath (10) defined by circumferen...
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WO/2016/031475A1 |
An axial-direction passage (45), a forced vortex passage (46), a first blade array passage (47), and a second blade array passage (48) are formed in a rotor shaft (32) of a turbine (30). Cooling air from an air extraction port (16) of a ...
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WO/2016/030307A1 |
The invention relates to a turbine blade (1) with an internally cooled turbine airfoil (3), in which a hollow space (10) is divided by rib elements (11, 12) into at least one cooling channel (13) carrying coolant, wherein at least one of...
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WO/2016/030449A1 |
The invention relates to a turbine blade (1) with an internally cooled turbine blade airfoil (3), in which a hollow space (10) is divided by rib elements (11, 12) in at least one cooling channel (13) carrying a coolant (14), wherein a re...
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WO/2016/032881A1 |
A rotor for use with an airborne wind turbine, wherein the rotor comprises a front flange, a can, a rear flange, and a rigid insert comprising a propeller mount, wherein the front flange, can, and rear flange comprise one of carbon fiber...
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WO/2016/032789A1 |
An article for high temperature service is presented herein. One embodiment is an article including a substrate having a silicon-bearing ceramic matrix composite; and a layer disposed over the substrate, wherein the layer includes silico...
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WO/2016/033465A1 |
A turbine blade (10) includes an airfoil (12) extending span-wise along a radial direction, and a shroud (26) positioned along a tip (22) of the airfoil (12) extending generally along a circumferential direction, scalloped, across a pres...
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WO/2016/030231A1 |
The present invention relates to a method for manufacturing a turbine assembly (10) comprising at least one aerofoil unit (12) comprising at least a basically hollow aerofoil (14) with at least one cooling passage (16) for a cooling medi...
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WO/2016/031268A1 |
A turbocharger (1) is provided with a valve body (10) which is disposed in a suction flow path (Cb) leading from an inflow port (14) of a housing (4a) covering a turbine rotor blade (6) to a scroll flow path (Ca) and composed of a single...
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WO/2016/030613A1 |
The invention relates to a diffuser vane (2) for a gas turbine engine, comprising a vane assembly (4) made of a composite material having a fibrous reinforcement densified by a matrix, the fibrous reinforcement being obtained from long f...
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WO/2016/030608A1 |
The invention relates to a guide vane (10) made from composite material for a gas turbine engine, comprising a fibrous reinforcement densified by a matrix, the fibrous reinforcement being formed as a single component by means of three-di...
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WO/2016/030289A1 |
The invention relates to a turbine blade for a turbomachine comprising a turbine blade wall (1) and a fluid channel (2) having an inlet channel section (2a) on the end region leading to the cold side, an outlet channel section (2b) on th...
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WO/2016/030157A1 |
The present invention relates to a turbine assembly (10, 10a, 10b) comprising a basically hollow aerofoil (12) having at least a main cavity (14) with at least an impingement tube (16, 16b), which is insertable inside the main cavity (14...
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WO/2016/026814A1 |
A compressor aerofoil (70) for a turbine engine or an axial process compressor, the compressor aerofoil comprises a suction surface wall (88) having a suction surface (89) and a pressure surface wall (90) having a pressure surface (91), ...
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WO/2016/028543A1 |
A method, including: replacing an original blade shelf (16) of a gas turbine engine blade (10) with a new blade shelf (64) that is located closer to a base (18) of the blade than the original blade shelf; adding mass to the blade until a...
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WO/2016/028306A1 |
A modular turbine blade assembly (10) usable in a gas turbine engine (12) and formed from an airfoil (28) and an independent, modular platform (16) supported by one or more clevis arm supports (14) extending radially inward from the modu...
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WO/2016/025253A1 |
A method for forming a coating on a substrate is provided. To an assembly 10 including a substrate 12, a porous matrix 14 on the substrate 12, and an impregnating material 16 on or within the porous matrix 14, the method includes applyin...
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WO/2016/025130A1 |
A method, including: providing a layer of powder material (106) on a substrate (12) having protruding rib material (26); and traversing an energy beam (100) across the layer of powder material to form a cladding layer (10) around and bon...
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WO/2016/025133A1 |
A method, including: providing a layer of powder material (156) on a substrate (130); and traversing an energy beam (15) across the layer of powder material to form a cladding layer (10), wherein the cladding layer forms a layer of an ai...
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WO/2016/023850A1 |
The invention relates to a system for introducing mechanical counter vibrations into a rotating rotor shaft of a turbine, comprising: - at least one measurement unit configured to detect mechanical vibrations of the rotor shaft and to ge...
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WO/2016/024458A1 |
In the present invention, an axial flow-type turbo machine is provided with: a plurality of blades (12) that form a stationary blade row or a moving blade row; an end wall (30) to which the plurality of blades (12) are fixed and which fo...
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WO/2016/019468A1 |
A structure adapted to traverse a fluid environment includes an elongate body having a root, a wingtip, a leading edge and a trailing edge; and a plurality of rigid projections each extending from a respective position along the leading ...
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WO/2016/022126A1 |
A cooling system (10) for a turbine airfoil (12) of a gas turbine engine having a bifurcated mid-chord cooling chamber (16) for cooling the airfoil (26) is disclosed. The bifurcated mid-chord cooling chamber (16) may be formed from a pre...
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WO/2016/022140A1 |
A component wall (10) includes a substrate (12) having a first surface (14) and an opposed second surface (16), and at least one cooling passage (20) extending through the substrate (12) for delivering cooling fluid (CF) from a chamber (...
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WO/2016/020614A1 |
The invention relates to a turbomachine turbine blade (1) comprising a suction face (11), a pressure face (12), a leading edge (13) and a trailing edge (14) as well as a squealer (2) at the tip thereof, said squealer tip (2) comprising a...
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WO/2016/018570A1 |
An article includes a substrate, a substantially hermetic sealing layer disposed on the substrate, and a porous transition layer disposed on the substrate between the sealing layer and the substrate. The article also includes one or more...
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WO/2016/016545A1 |
The invention relates to a turbomachine element comprising a stator (2), a rotor (1), and a first sealing means (9) for sealing between the rotor (1) and the stator (2) arranged to be active when the rotor is in the operating position of...
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WO/2016/015920A1 |
A turbine aerofoil (1) comprises: - a leading edge (3), - a trailing edge (5), - an exterior surface including a suction side (7) and a pressure side (9), - at least an internal cavity (11A-11D) for forming a cooling circuit comprising c...
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