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WO/2021/151951A1 |
An outlet guide vane (OGV) structure for a gas turbine engine comprises a plurality of radially extending guide vanes (30), at least one guide vane comprises at least one inlet (35) allowing air to pass into at least one internal cavity ...
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WO/2021/148077A1 |
The invention relates to a sealing-air apparatus (10) for a turbomachine (100), comprising a sealing device (20) for sealing a sealing gap (50) between two components (30, 40) of the sealing-air apparatus (10) with respect to a sealing-a...
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WO/2021/148739A1 |
The invention relates to a stator wheel (20) for a turbine of a turbomachine. This wheel (20) comprises an inner shroud (22) formed by an upstream portion (23) and a downstream portion (24) which are configured to be assembled with the b...
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WO/2021/148441A1 |
The invention relates to an assembly for a turbine engine extending along an axis and comprising: - a combustion chamber (1) comprising, at the downstream end thereof, a downstream flange (6) comprising a radially extending part; - a dis...
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WO/2021/139939A1 |
The invention relates to a guide vane ring (1) which is divided into an upper and into a lower guide vane ring half, with an inner ring (2) which is split at least in two, has a substantially U-shaped cross section, and forms a radially ...
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WO/2021/131167A1 |
The purpose of the present invention is to provide a Co-based alloy product having equivalent or higher mechanical properties to or than those of a precipitation strengthened Ni-based alloy material. The Co-based alloy product according ...
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WO/2021/123577A1 |
The invention relates to a method for manufacturing a metallic turbomachine bladed disk (blisk) reinforced with an insert made of a metallic matrix composite material, said method comprising the following step: - (E1): winding ceramic fi...
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WO/2021/121976A1 |
The invention relates to a gas turbine engine (1) of an aircraft, comprising an inner engine region (27) and an outer engine region (28), which delimit a flow cross-section (2) and are operatively interconnected by means of braces (22, 2...
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WO/2021/126478A1 |
A turbocharger having a turbine housing including an outer surface and an inner surface defining an exhaust passage, an exhaust inlet port in fluid communication with the exhaust passage, and a tucked exhaust inlet flange surrounding the...
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WO/2021/117883A1 |
This turbine stator vane extends in the radial direction which intersects the flow direction of steam, and includes a middle surface facing the upstream side in the flow direction, and a back surface facing the downstream side in the flo...
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WO/2021/118853A1 |
A casing half shell for a turbine system, a steam turbine system and related method are provided. The casing half shell includes a body having an open interior for enclosing parts of the turbine system; a first inlet in the body for deli...
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WO/2021/115658A1 |
The invention is about a combustion chamber (01) of a gas turbine, wherein downstream of the combustion chamber (01) an expansion turbine with a turbine inlet (08) is arranged. The combustion chamber (01) has an annular design with an co...
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WO/2021/110192A1 |
The present invention relates to a guide vane arrangement (20) for a turbomachine (1), with a guide vane blade (21) which has a pressure side surface (36) and a suction side surface (35), wherein the guide vane blade (21) is mounted such...
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WO/2021/111059A1 |
Disclosed is an electrically conductive rigid bar (80) for electrically connecting an electric machine (70) of an aircraft turbine engine, characterised in that it comprises: - an elongate body (80a) made from electrically conductive mat...
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WO/2021/111060A1 |
Electric module (50) for an aircraft turbomachine (10), said module comprising: - an electric machine (70) stator (70b), said stator having an annular shape around an axis (A) and being intended to surround a rotor (70a) of the electric ...
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WO/2021/112064A1 |
Provided is a steam turbine member in which the adhesion of scales is minimized without compromising the corrosion resistance, etc., of the turbine. A steam turbine member comprising an amorphous carbon vapor deposition film at a site ...
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WO/2021/111058A1 |
Aircraft turbine engine (10) comprising: - a gas generator (12) having a longitudinal axis (A), - a fan (14) which is located at an upstream end of the gas generator and which is configured to rotate about the axis, and - an electric mac...
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WO/2021/111061A1 |
Disclosed is an aircraft turbine engine (10), comprising: a gas generator (12) having a longitudinal axis (A), a fan (14) located at an upstream end of the gas generator and configured to turn about said axis, and an electric machine (70...
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WO/2021/099482A1 |
The present invention relates to a front centre body (FCB) structure for a geared turbofan engine. The FCB comprises a plurality of vanes extending across the inlet duct to the low pressure compressor and integrates a heat exchanging arr...
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WO/2021/101648A1 |
Embodiments of the present disclosure generally relate to protective coatings on turbine blades, turbine disks, and other aerospace components and methods for depositing the protective coatings. In one or more embodiments, a turbine blad...
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WO/2021/094406A1 |
A pin member is proposed for a turbo-machine having a shroud arranged to rotate within a turbine housing. The pin member is configured to limit this rotation. It is a one- piece element comprising a cylindrical body and a limit surface f...
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WO/2021/089933A1 |
The invention relates to a device for connecting parts of an aircraft engine. The connection device comprises connectors suitable for connecting a first and a second part so as to establish a physical transfer link between these parts an...
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WO/2021/084203A1 |
The invention relates to a turbine (1) comprising a casing, an outer metal shroud (9), an inner metal shroud (5) and an annular distributor (2) having a plurality of CMC ring sectors (20), each sector comprising a mast (6), an inner plat...
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WO/2021/083442A1 |
The present invention relates to a guide vane assembly for a turbomachine, in particular a compressor stage or turbine stage of a gas turbine, comprising at least one guide vane that is adjustable about a rotational axis (D), the vane bl...
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WO/2021/080680A1 |
An embodiment of an independent cooling circuit for selectively delivering cooling fluid to a component of a gas turbine system includes: a plurality of independent circuits of cooling channels embedded within an exterior wall of the com...
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WO/2021/080679A1 |
A coolant delivery system for a component of a gas turbine system includes: a plurality of independent circuits of cooling channels embedded within an exterior wall of the component, each independent circuit of cooling channels including...
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WO/2021/069816A1 |
The invention relates to a nozzle (20) for a turbomachine turbine. The nozzle (20) comprises blades (40) made of ceramic matrix composite material, and at least one metal liner (70) passing through a respective blade (40). The liner (70)...
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WO/2021/067979A1 |
A composite layer system is presented. The composite layer system includes a metallic substrate, a structured surface, and a thermal protection system. The structured surface may be additively manufactured onto the metallic substrate and...
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WO/2021/067978A1 |
A hybrid three-layer system is presented. The hybrid three-layer system includes a two-layer composite system and an additively manufactured third layer comprising a lattice structure. The composite layer system includes a metallic subst...
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WO/2021/058882A1 |
The invention concerns an aircraft turbine engine (1), comprising a gas generator comprising at least one annular gas flow duct (2), the duct (2) being defined by two annular housings, respectively an external housing (3b) and an interna...
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WO/2021/060093A1 |
In a turbine blade (1) provided with a cooling passage (11) configured such that a cooling medium (CL) travels from a root portion side to a tip end portion side in a blade height direction (H), and a lattice structure (21) in which a pl...
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WO/2021/055200A1 |
A vane of a turbine system is provided. The vane includes: an internal cavity configured to receive a flow of cooling fluid; a variable thickness wall adjacent the internal cavity; and an impingement plate separating the variable thickne...
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WO/2021/048508A1 |
The invention relates to a method for manufacturing a hollow part made of composite material for an aircraft turbomachine, wherein: a) a preform is produced by the three-dimensional weaving of threads; b) the preform is cut so as to prov...
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WO/2021/043527A1 |
The invention relates to a seal (01) for sealing a gap in a combustion apparatus of a gas turbine between a first side (02) and an opposite second side (03). The seal comprises a steel strap (05) with a flat shape and a first metal web (...
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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/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/2021/025831A1 |
This disclosure provides a seal assembly (230, 330, 431, 530, 630, 730) to provide a generally smooth transition from a combustion chamber (390) to a turbine (400) within a gas turbine engine (100). A seal body (232, 332, 32, 532, 632, 7...
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WO/2021/020518A1 |
This steam turbine is provided with: a rotary shaft; a plurality of movable blades each of which has a movable blade body (42) and a shroud (43), and which are circumferentially arranged at intervals; a casing (5) that has a recessed sec...
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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/2021/018495A1 |
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/2021/004562A1 |
The invention relates to a guide vane segment (40) for a gas turbine (10), in particular an aircraft gas turbine, comprising: at least one guide vane (46); a radially inner cover strip (44); and a radially outer cover strip (42), the at ...
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WO/2021/005042A1 |
A turbine assembly for a turbocharger is disclosed. The turbine assembly comprises a housing and a vane assembly. The housing defines a flow path between an inlet and an outlet, the housing extending around an axis. The housing comprises...
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WO/2020/260633A1 |
There is provided a variable geometry turbine comprising: a turbine wheel supported for rotation about a turbine axis; a turbine housing comprising a first volute for receiving a first exhaust gas stream from a first fluid source and a s...
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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/2020/261628A1 |
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/2020/254764A1 |
One aspect of the invention relates to a method (200) for coating a vane (100) of a guide vanes assembly (30) of a turbomachine (1), the vane comprising a root (103) and a tip (104), an extrados face (105) and an intrados face (106) whic...
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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/2020/249915A1 |
The present document concerns an assembly (46a, 46b) for a gas turbine comprising a nozzle having radial blades (54) linked at their radially inner ends to an inner annular platform (52) and at their radially outer ends to an outer annul...
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WO/2020/249886A1 |
The invention relates to a turbine (1) having a casing and a nozzle (2), comprising an outer metal shroud (9) rigidly connected to the casing, an inner metal shroud (5), and a plurality of CMC nozzle sectors (20) forming a ring extending...
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WO/2020/250635A1 |
A supercharger (1) comprises: a diagonal flow turbine (31) including a turbine impeller (35); a turbine housing (33) that includes a gas flow channel (42) extending toward a leading edge (39a) of a moving blade (39) of the turbine impell...
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