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WO/2021/039090A1 |
This high-frequency hardening apparatus is provided with: an induction heating coil which has a U-shaped part that sandwiches a turbine blade, a pair of linear parts, and a connection part connecting the U-shaped part and the linear part...
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WO/2021/032273A1 |
A multi-stage turbocharging assembly (100) is described. The multi-stage turbocharging assembly (100) includes a high-pressure stage (110) including a high-pressure turbine (113) coupled with a high-pressure compressor (114). Additionall...
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WO/2021/033564A1 |
A stator blade (50) comprises a blade body (51) and a shroud (60i). The shroud has a gas path surface (64), a leading-end surface (62f), a leading-end corner (66) that is the corner of the gas path surface and the leading-end surface, a ...
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WO/2021/032924A1 |
Device for distributing oil from a rolling bearing (8) for an aircraft turbine engine, comprising: - a rolling bearing (8) comprising two rings (12, 14), respectively an inner ring and an outer ring, - an oil distribution ring (5) config...
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WO/2021/028307A1 |
The present invention relates to a device for cooling, using air jets, an external casing (154) of a turbomachine, comprising a housing (20) for supplying air to cooling tubes (22) of said casing, the housing being provided with an attac...
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WO/2021/030021A1 |
The present subject matter is directed to an axial retention assembly for combustor components of a gas turbine engine. The axial retention assembly may include a combustor having a liner (38) defining a liner aperture (114) extending th...
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WO/2021/028634A1 |
The invention concerns an assembly (25) for a turbomachine turbine comprising a casing (18) comprising an annular wall (26) extending about an axis, and means for cooling the casing (18), the cooling means comprising a manifold housing (...
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WO/2020/046376A9 |
A cooling channel arrangement for a turbine engine transition exit frame is de-scribed. The cooling arrangement includes a primary cooling channel in fluid communication with a source of cooling fluid. A turbulent flow chamber in fluid c...
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WO/2021/025524A1 |
Disclosed are an impulse turbine and a turbine device. The disclosed impulse turbine includes a cylindrical body having an axial hole, and a blade unit arranged to surround the circumference of the body. The blade unit includes a cylindr...
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WO/2021/023470A1 |
Disclosed is a compressor (1) of a dual-flow aircraft turboshaft engine extending longitudinally along an axis X, the compressor (1) comprising a low-pressure compressor, a high-pressure compressor (3) and an intermediate casing (2) axia...
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WO/2021/021231A1 |
A method of forming a component includes mixing a powdered base material and a binder to define a mixture, forming the mixture into a desired shape without melting the base material, removing the binder from the desired shape to define a...
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WO/2021/021206A1 |
A method for attaching a first component composed of a ceramic matrix composite (CMC) to a second component composed of a metallic substructure is provided. The first component comprises at least two slots formed within a body of the fir...
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WO/2021/020372A1 |
An acoustic attenuator (61A) comprises a first attenuation unit (71A), a second attenuation unit (63), a welded section (W1), and a communication part (64A). A first acoustic damper (74) is provided on an outer surface of a first acousti...
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WO/2021/020098A1 |
This method for cleaning the blades of a rotary device includes: a first coating step in which blades are coated with a water-soluble cleaning liquid containing a surfactant; a standstill step in which the blades coated with the cleaning...
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WO/2021/018333A1 |
The invention relates to a module (20) for a turbomachine (1), having two components (21, 22), which each extend peripherally and are segmented, wherein the components (21, 22) have an axial overlap (40) and have a radial offset (41) rel...
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WO/2021/021287A1 |
A high temperature flange joint (30) in a gas turbine engine (1) includes a first flange (34a) formed on a first component (32a) abutting a second flange (34b) formed on a second component (32b). The flange joint (30) includes multiple a...
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WO/2021/018495A1 |
The invention relates to a method for upgrading a gas turbine (1), said method comprising the steps of: a) removing all guide vanes (4) of the first guide vane stage; b) replacing the removed guide vanes (4) of the first guide vane stage...
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WO/2021/020170A1 |
A plant monitoring device (20) is provided with: a state quantity acquiring unit (211) which acquires state quantities for each of a plurality of characteristic items relating to a plant; an abnormality degree calculating unit (212) whic...
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WO/2021/021232A1 |
A blade for a gas turbine includes a removed portion space, and further includes an airfoil portion defining the removed portion space, the airfoil portion formed from a base material, and a replacement component formed to fill the remov...
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WO/2021/018698A1 |
The invention relates to a bearing unit (10) of a rotor shaft (30) for a charging apparatus (50) of an internal combustion engine, a charging apparatus (50) having such a bearing unit (10) and a disassembly method for such a bearing unit...
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WO/2021/015861A1 |
A gas turbine engine having a pre-swirler (400) adjustability is presented. The pre-swirler includes a pre-swirler insert (420) installed in a component enclosed by a cover (12, 16). The component includes an inner compressor exit diffus...
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WO/2021/014903A1 |
A steam stop valve (20) is provided with: a valve body (40) that linearly moves in a reciprocating manner in a valve casing (30) and opens/closes a flow passage (33); a valve rod (41) that is connected to the valve body; an actuator (50)...
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WO/2021/009464A1 |
Tool (100) for disassembling and moving a TRV-type turbine casing (24) from an aircraft turbine engine (10), said turbine casing comprising two annular shrouds, inner (24a) and outer (24b) shrouds respectively, which extend one inside th...
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WO/2021/008816A1 |
The invention relates to a turbine casing for an exhaust-gas turbine, which turbine casing has a connection flange for bearing-casing-side attachment to a bearing casing in which casing-connection holes that are mutually spaced in the ci...
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WO/2021/009226A1 |
The invention relates to a depolluted test bench (1) for a turbomachine (6) comprising: - a channelled air duct (2) comprising an air inlet (3) and an air outlet (4) to allow a flow of air between the air inlet (3) and the air outlet (4)...
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WO/2021/011195A1 |
The present disclosure is directed to an axial retention assembly for combustor components of a gas turbine engine. The axial retention assembly may include a combustor having a liner and a casing, with the casing including a flange spac...
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WO/2021/009457A1 |
Method for producing a casing (3) for an aircraft turbine engine, said casing comprising an annular shell (9) extending about an axis A and made of a composite material, an annular layer (4) comprising an abradable material arranged insi...
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WO/2021/009953A1 |
Provided is a gas turbine system 100 equipped with: a compressor (10) that compresses external air to generate compressed air; a combustor (20) that burns the compressed air generated by the compressor (10) with fuel to generate combusti...
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WO/2021/007056A1 |
A flow regulating system (200) for increasing a flow of cooling fluid (140, 202) supplied to a cooling system of a component of a gas turbine system (10) is provided. The flow regulating system (200) includes: a pneumatic circuit (206) e...
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WO/2021/001068A1 |
The invention relates to a turbine housing (1) which is divided into a first turbine housing part (2) and a second turbine housing part (3) in a radial direction, wherein at least one guide equipment support piece (4) for receiving a gui...
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WO/2021/001610A1 |
The invention relates to a device (16) for damping a rolling bearing, comprising a support (18) and a radially flexible cage (17). The cage (17) comprises a ring (20) provided in order to be mounted on the periphery of a rolling bearing....
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WO/2021/001065A1 |
The invention relates to a bearing assembly (21, 22) for a turbo-engine, comprising a bearing and parts of a bearing temperature detecting device (60), the bearing comprising: a main body (24) having a thermoplastic bearing layer (28) th...
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WO/2021/001609A1 |
A pump (12), which can be a gear pump driven by a rotating body of an aircraft turbomachine such as a blower shaft, is always rotated in the same direction, thanks to a transmission comprising an oblique double gear (19) which is formed ...
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WO/2021/001615A1 |
Disclosed is a device for cooling a turbine (1) shroud, comprising: - at least one annular flange (33, 34) configured to be attached to an annular radial collar (32) of a shroud support structure (3), being arranged upstream of the turbi...
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WO/2020/260808A1 |
The invention relates to an aircraft turbomachine (10) comprising a lubricating circuit (22) notably comprising a reservoir (24) of lubricating fluid, a pump (26) drawing lubricating fluid from the reservoir (24) to inject it toward seve...
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WO/2020/260796A1 |
Turbomachine output bearing support (10) extending in an axial direction (X), said support (10) being formed in a single part and comprising an annular inner wall (12) and having an inner side (CI) and an outer side (CE), an annular oute...
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WO/2020/260804A1 |
A method for manufacturing a component of revolution made of composite material comprises: - using multilayer or three-dimensional weaving to create a fibrous texture (140) in the form of a tape, - winding the fibrous texture (140) over ...
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WO/2020/263394A1 |
An outlet guide vane assembly in a gas turbine engine is presented. The outlet guide vane assembly includes an inner shroud and an outlet guide vane having an inner platform. The inner shroud has a flange arranged at aft side that is bol...
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WO/2020/260835A1 |
Method for manufacturing a housing (3) for an aircraft turbine engine, said housing comprising: • - an annular body (30) extending around an axis A and comprising a securing flange (31, 32) extending radially outwards at each of the ax...
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WO/2020/261628A1 |
A stator vane support ring (52) supports radially inward ends of a plurality of stator vanes (32) disposed in a circle, the support vane support ring (52) comprising a semiannular first body section (50A) and a semiannular second body se...
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WO/2020/249887A1 |
A component (1, 2) for supporting at least one bearing (3) for a turbine engine (10) comprising: - two coaxial walls, internal (4) and external (5) walls respectively, defining a gas flow vein (6) between them and interconnected by a row...
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WO/2020/249399A1 |
The present invention relates to a bypass fan casing (4), characterised in that it comprises a single wall (14) configured to form at least part of an outer skin of a nacelle (17), said wall (14) comprising at least one reinforcement (13...
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WO/2020/249599A1 |
The invention regards a gas turbine engine for an aircraft that comprises a nacelle, a fan, an engine core, a bypass duct extending between the engine core and the nacelle and guiding a bypass airflow through the bypass duct, and at leas...
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WO/2020/252226A1 |
A vibration absorber damper and method of dissipating vibration energy in a rotatable structure which is nominally cyclic symmetric. The nominally cyclic symmetric structure includes a hub portion having a rotational axis and a plurality...
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WO/2020/249431A1 |
A rotor support (5) configured to rotatably mount a rotor shaft (20) in a vacuum pump is disclosed. The rotor support (5) comprises: a rolling bearing (10) for rotatably supporting the shaft (20); an insert (70) and at least one resilien...
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WO/2020/249888A1 |
The present invention concerns an inlet cone (10) for an aircraft turbine engine (1), comprising a frustoconical body (12) and a tip (11) made from elastically deformable material attached to an end (12p) of smaller diameter of the body ...
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WO/2020/250596A1 |
This steam turbine stationary blade is provided with: a blade body part having a blade surface including a pressure surface and a negative pressure surface; a moisture removal flow passage provided inside the blade body part; at least on...
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WO/2020/246413A1 |
The present invention provides a turbine blade, a turbine blade production method, and a gas turbine. The turbine blade has a cooling passageway provided along the blade height direction. The cooling passageway has: a first cooling hole ...
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WO/2020/245528A1 |
The invention relates to an assembly (10) for supporting and guiding a drive shaft (1) for an aircraft turbine engine, comprising a bearing support (3) having a cylindrical housing (30) for receiving an outer ring (21) of a bearing (2), ...
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WO/2020/246156A1 |
A gas turbine blade repair method including: a step in which a thermal barrier coating is removed to expose at least part of a base material of a gas turbine blade; a first etching step in which the exposed base material is etched; a fir...
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