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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/2021/015861A1 |
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/2021/013920A1 |
The present invention relates to a method for continuously manufacturing an abradable sealing element (4), this element comprising a support substrate (40a, 40b) covered by a coating comprising at least two successive layers, each compri...
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WO/2021/013281A1 |
The invention relates to a rotor blade (20) to be arranged in a gas conduit (3) of a turbomachine (1), having a rotor blade airfoil (23), which radially inwardly has a chord length Si, radially outwardly has a chord length Sa, and in a r...
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WO/2021/013280A1 |
The invention relates to an intermediate element (10) for a blade/rotor disc connection in a rotor of a turbomachine, in particular in a rotor of a power plant, the intermediate element (10) being adapted to the shape of a blade root (30...
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WO/2021/013282A1 |
The invention relates to a rotor blade (20) for arranging in a gas channel (3) of a turbomachine (1), comprising a rotor blade sheet (23) which has a leading edge (23a) and a trailing edge (23b) downstream therefrom with respect to a flo...
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WO/2021/013279A1 |
The present invention relates to an integrally bladed rotor for a turbomachine, in particular a compressor or turbine stage of a gas turbine, to which at least one separately formed impulse body housing (40; 40') is fastened by means of ...
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WO/2021/009157A1 |
A method of bonding a composite vane (1) to at least one support (2). The method comprises the steps of positioning an end of a vane (1) within a support (2), causing an adhesive to flow between the vane and the support from an inlet (3)...
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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/2021/008842A1 |
A blade for a turbomachine fan, the blade (1) being made from a composite material containing a plurality of longitudinal conductive fibres (F) embedded in an electrically non-conductive matrix, the blade (1) having at least one fastenin...
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WO/2021/008901A1 |
A shaft connection (50) comprises: a female component (51) with an internal spline toothing system (52), and a male component (55) with an external spline toothing system (56) which can be brought into engagement with the internal spline...
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WO/2021/008815A1 |
The invention relates to a blade ring (2) for an axial turbomachine, comprising a blade support (6) with a number of holding grooves (8) for rotor blades (10), said grooves running in the axial direction (A), and a corresponding number o...
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WO/2021/005286A1 |
Disclosed is a process for manufacturing a fibrous preform for a part made of composite material, comprising creating a fibrous texture (200) by three-dimensional or multilayer weaving between a plurality of weft layers (202) and of warp...
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WO/2021/005312A1 |
The present invention relates to a blower vane (1) of a turbomachine, comprising a structure made of composite material which comprises a fibrous reinforcement (11) and a matrix in which the fibrous reinforcement (11) is embedded. The va...
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WO/2021/007055A1 |
A method for creating a three-dimensional (3D) mark in a protective coating including at least one of a TBC and a bond coating over a metal part, is provided. The method may include positioning a mask over the protective coating, the mas...
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WO/2021/004821A1 |
The solution proposed relates in particular to an engine component (3), having at least one first loading zone (33), which is designed for dynamic loads arising on the engine component (3) when the engine component (3) is correctly built...
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WO/2021/001611A1 |
A fibrous reinforcing structure for a part made of composite material woven as a single piece by three-dimensional or multi-layer weaving between a plurality of layers of weft filaments (202) and a plurality of layers of warp filaments (...
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WO/2020/260258A1 |
The invention relates to a structural assembly for a gas turbine engine (10), which structural assembly comprises a fan (23) and a forked fan shaft (7), which is coupled to the fan (23) and comprises a radially outer fan shaft (71) and a...
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WO/2020/263396A1 |
A turbine airfoil (10) includes an airfoil body (12) and a generally hollow flow displacement element (30) positioned in an interior portion of the airfoil body (12) and extending along a span-wise extent thereof. The flow displacement e...
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WO/2020/261272A1 |
A system and method for determining the condition of a thermal barrier coating on a base metal component, comprising the use of an induction coil to input into the metallic base layer through the coating layer, a temporally varying heat ...
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WO/2020/260805A1 |
The invention relates to a metal core (20) for high-temperature shaping of a metal part made of titanium-based alloy. The metal core (20) has a layer of material enriched in metal carbonitride on an outer surface (23) intended to come in...
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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/2020/249686A1 |
The present invention concerns a dynamic balancing device (1) for a rotor, the rotor being able to rotate relative to a housing around a longitudinal axis (X-X), the device (1) comprising: - a support shaft (100) suitable for being fixed...
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WO/2020/249148A1 |
The present invention relates to a method for producing a rotary disc or a blisk for a high-pressure compressor or a high-speed turbine, in particular a low-pressure turbine of an aircraft engine, in particular a geared turbofan engine, ...
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WO/2020/249627A1 |
The present invention refers to an optimized blade comprising an anchor element to be used in a streaming engine. Addition- ally, the present invention refers to the method of manufac- turing such blade. Furthermore, the present inventio...
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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/2020/249886A1 |
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/2020/249905A1 |
The invention concerns a turbine blade, comprising a root, a vane (12) comprising a leading edge and a trailing edge (17) and a pressure-side wall and a suction-side wall, and comprising cooling vents (26, 27) at the trailing edge (17), ...
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WO/2020/249914A1 |
The invention relates to a vane for a turbine engine of an aircraft comprising a blade having a lower surface and an upper surface that are connected upstream, in a direction of circulation of a gas in the turbine engine, by a leading ed...
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WO/2020/250674A1 |
Provided is a rotor, for example, with which it is possible to suppress causes of fluid turbulence and to suppress stress concentrations. In a rotor (50) having formed therein a groove (52) with which a moving blade (24) including a dove...
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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/2020/246413A1 |
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/2020/246494A1 |
This film cooling structure comprises a wall part 20, and a cooling hole 30 that is inclined such that an outlet 32 is located further rearward than an inlet 31. The cooling hole 30 includes a straight pipe part 30 and a diffuser part 34...
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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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WO/2020/245551A1 |
The invention relates to the manufacture of an aeronautics part (5) by injection molding. After having injected the prepared mixtures so as to obtain two green blanks, an assembly zone (9a, 9b) of the at least one of these two blanks is ...
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WO/2020/244691A1 |
The present invention relates to a method for producing an impulse body module for a gas turbine, which has a housing (10) with at least one cavity (11), in which the at least one impulse body (2) is accommodated with room for movement, ...
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WO/2020/246289A1 |
A film cooling structure 10 has a wall section 20 that extends from front to rear, and a cooling hole 30 that has a tubular inner peripheral surface 31 and is inclined such that the outlet 33 is located more rearward than the inlet 32. T...
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WO/2020/239803A1 |
Disclosed is an assembly for a turbomachine comprising: • a first rotor comprising: • a disc (120), and • a plurality of vanes (122) capable of fluttering relative to the disc (120), • a second rotor (140), and • a damper (2) c...
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WO/2020/242675A1 |
A turbine blade (440a, 440b) having a base (442) and an airfoil (441), the base including a root end (444). The airfoil including a skin (460) extending from the base and defining a leading edge (446), a trailing edge (447), having a tip...
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WO/2020/239804A1 |
The present invention relates to a turbomachine assembly, comprising: - a casing (10), - a first rotor (12) which is movable in rotation with respect to the casing (10) about a longitudinal axis (X-X), and comprising: * a disk (120), and...
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WO/2020/239151A1 |
The present document describes a rotor blade (10) for a gas turbine, in particular an aero gas turbine, having a blade portion (12) and a blade root (14) that is connected to the blade portion (12), wherein the blade root (14) has, in re...
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WO/2020/239808A1 |
The present invention relates to an assembly for a turbomachine, comprising: • - a first rotor, • - a second rotor, and • - a damper (2) configured to damp a displacement of the first rotor relative to the second rotor, the damper ...
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WO/2020/239559A1 |
A heatshield for a gas turbine engine. The heatshield comprising a main body having a leading edge, a trailing edge, lateral edges, a first surface and a second surface, the first surface being exposed to a hot working gas in use passing...
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WO/2020/239369A1 |
During a mixture of a nickel based super alloy a MCrALY composition and a praise alloy a good composition is found for welding or for additive manufacturing.
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WO/2020/241133A1 |
A rotor disc (60) has diametrically outer surfaces (63, 75b), a diametrically inner surface, a plurality of blade root grooves (64) recessed diametrically inward (Dri) from the diametrically outer surfaces (63) and aligned in a circumfer...
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WO/2020/239490A1 |
The invention relates to a turbine vane of a turbine engine which comprises a blade (11) and a root (12), the root comprising a stilt (13) having lateral flanks with a curvilinear profile, said stilt comprising a frangible zone suitable ...
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WO/2020/233947A1 |
The invention relates to an assembly for a turbomachine (2), comprising a turbine nozzle (10) which comprises a tubular platform (102), an inner radial flange (103) extending radially inward from the platform (102), and a plurality of va...
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WO/2020/233832A1 |
The invention relates to a method for applying a coating (1) onto the surface (2) of a mullite material (3), having the steps of pre-treating the surface (2) of the mullite material (3) by means of a plasma-chemical process in which mole...
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WO/2020/234295A1 |
The invention relates to a method for producing a component (10), which method comprises: a) the additive manufacturing of a shaped body (11) for the component (10), in particular from a powder bed (P); b) the forming of risers (12) and/...
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WO/2020/236168A1 |
A molding tool (10) for manufacturing cooling features in a ceramic core for a casting process includes a first mold portion (12) comprising a crossover hole forming feature (18); a second mold portion (24) comprising an impingement jet ...
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