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WO/2021/150418A1 |
A turbine rotor blade is additively manufactured and includes an airfoil body including a concave pressure side outer wall and a convex suction side outer wall that connect along leading and trailing edges. A shank is at a radial inner e...
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WO/2021/140292A1 |
Method for controlling a clearance between blade tips of an aircraft engine turbine rotor and a turbine shroud, which comprises estimating the clearance to be controlled and controlling a valve supplying a flow of air to the turbine shro...
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WO/2021/122926A1 |
The present invention relates to a valve arrangement. The present invention further relates to a fluid flow control element. Furthermore, the present invention relates to a turbomachine system comprising such a valve arrangement and/or f...
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WO/2021/120772A1 |
Disclosed is a labyrinth sealing device capable of reducing the amount of gas intrusion, the device comprising a rotation shaft (1), wherein a sealing bush (2) is coaxially sleeved on the outside of the rotation shaft (1); a plurality of...
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WO/2021/115510A1 |
The invention relates to a rotor (10) for a turbomachine (100), having at least one blade and having at least one rotor main part (20) which has at least one recess (22) in which a blade root (40) of the at least one blade is interlockin...
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WO/2021/118398A1 |
The invention may be used in the field of gas supply to recover energy from a stream of compressed natural gas while simultaneously producing mechanical energy and cooling capacity. A turboexpander power unit comprises a turboexpander co...
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WO/2021/115626A1 |
The composite seal structure includes a carrier ring (33) and a seal element (35) housed in an annular groove formed between a circumferential outer wall and two side walls of the carrier ring (33). The seal element has a first region in...
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WO/2021/118414A1 |
A honeycomb seal of a turbomachine comprises a cartridge (1), segments (2), honeycomb units (3) and sealing ridges (4) of a rotor (5). The segments (2) are affixed in the cartridge (1) and provided with sealing ridges (6). The honeycomb ...
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WO/2021/116556A1 |
Disclosed is a turbomachine (10) with counter-rotating turbine for an aircraft, comprising: - a high-pressure body, - a low-pressure counter-rotating turbine (22), - a planetary-type mechanical epicyclic reduction gear (42), - guide bear...
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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/2021/110191A1 |
The invention relates to a seal carrier (50) for a turbomachine, in particular a gas turbine, having a carrier base (52) and at least one seal body (54), wherein the at least one seal body (54) is connected to the carrier base (52) and w...
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WO/2021/110353A1 |
The invention relates to a shaft sealing ring (1) comprising an outer circumference (2), an inner circumference (3) on which at least one sealing surface (4a-d) is formed, and two side faces (5a,b) axially opposing one another; on the fi...
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WO/2021/086847A1 |
A cryogenic device with a cartridge holder for a cryogen cartridge, cryogen cartridge is coupleable to a cryogen pathway; a probe receptacle for receiving a needle probe, wherein the probe receptacle is configured to couple the needle pr...
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WO/2021/083441A1 |
The present invention relates to a rotor blade arrangement for a turbomachine, with a rotor blade which has a sealing tip radially on the outside, and with a seal arrangement, wherein the seal arrangement forms a radially inwardly open c...
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WO/2021/073786A1 |
The invention relates to a rotor of a gas turbine comprising two adjacent rotor discs (01, 11), on each of which moving blades are fastened, an annular rotor component (21) being arranged between the rotor discs (01, 11) and having at it...
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WO/2021/063431A1 |
The invention describes a system with a rotor blade (40) for a gas turbine (10), more particularly an aircraft gas turbine, with: a blade foot (42), a blade neck (44) adjoining the blade foot (42) in the radial direction (RR); a blade ae...
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WO/2021/063552A1 |
The invention relates to a seal (01) for sealing a gap (09) in a combustion arrangement of a gas turbine. The seal (01) is formed by a L-shaped angle profile and a clamping profile. Both profiles have on the opposite side an engagement f...
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WO/2021/058908A1 |
The present invention relates to a device (10) for cooling a turbine casing with air jets, comprising: - a power supply unit (B), - at least one tube (T) having a first end (11) mounted on the wall (12) of the unit (B) such that the tube...
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WO/2021/052783A1 |
The present invention refers to a sealing element to be used in a continuous flow engine. Additionally, the present invention refers to a method of manufacturing such sealing element. Furthermore, the present invention refers to a contin...
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WO/2021/052517A1 |
The invention relates to a spring element for high-temperature applications, in particular for continuous-flow machines, such as gas turbines or aircraft engines, as well as corresponding continuous-flow machines, wherein the spring elem...
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WO/2021/055004A1 |
A turbine engine has: a first member (22) having a surface bearing an abradable coating, the abradable coating (36) being at least 90% by weight ceramic; and a second member (24) having a surface bearing an abrasive coating. The abrasive...
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WO/2021/048505A1 |
Turbomachine sealing ring (32) having an axis of revolution and comprising: - an annular support (34), - an annular coating (36) made of abradable material which is carried by said support, and - an annular thermal protection plate (40) ...
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WO/2021/048473A1 |
The invention relates to a method for manufacturing an aircraft turbine engine housing, the housing (23) comprising: - an annular shell (29) with axis A; - an annular element (24; 253, 254) attached to the inside of the shell (29), the a...
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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/2021/044614A1 |
This seal mechanism, which is inserted into a seal groove formed between mutually facing surfaces of two members, is provided with: a first seal member; a second seal member disposed so as to face the first seal member; and a deformation...
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WO/2021/040919A1 |
A damped turbine blade assembly (490, 491, 492, 493) for a gas turbine engine (100) is disclosed. The damped turbine blade assembly (490, 491, 492, 493) includes a damper (495, 496, 497, 498) positioned within a first small slot (481a) o...
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WO/2021/039811A1 |
A swirl breaker assembly according to one embodiment comprises: an annular body that extends along the circumferential direction; a flow guide that projects from the annular body in the axial direction, so as to extend along the circumfe...
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WO/2021/034370A1 |
The present invention relates to a non-contact seal assembly (400) for sealing a gap (11) between relatively rotatable components(13, 14) in a gas turbine engine. The non-contact seal assembly includes a primary seal (420) having a radia...
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WO/2021/033093A1 |
A dry gas seal (100) includes a mating ring (114) that can be coupled a the rotating shaft (102) to rotate with the rotating shaft, a retainer ring (117a) that can be fixedly attached to the compressor (104) and a carrier ring (170) move...
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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/2021/028307A1 |
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/2021/028634A1 |
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/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/2021/023927A1 |
Disclosed is a movable vane (1) for a wheel (2) of an aircraft turbine engine, the vane (1) comprising a blade (4) delimited by an outer heel (8) comprising a first seal (14), the vane (1) comprising an internal circuit (16) suitable for...
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WO/2021/023936A1 |
The invention relates to an abradable element (3) for a turbine of a turbomachine, comprising a layer (12) of cellular-structure material having walls (13) defining parallel wells (14) which extend through a wear face (21) of this layer....
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WO/2021/023945A1 |
The invention relates to a ring (1) for a turbomachine turbine, intended to surround a bladed disc (2) of a turbine rotor, said ring (1) extending circumferentially about an axis and comprising a radially outer annular support part (9) a...
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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/2021/021894A1 |
This disclosure is directed to composites of MAX-phase materials and gold, and methods for preparing the same.
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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/2021/015081A1 |
The purpose of the present invention is to suppress leakage of fluid and suppress a decrease in strength. A seal member (30) is disposed between a rotor (12) and a stator (11) to provide a seal between the rotor (12) and the stator (11)....
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WO/2021/009430A1 |
One aspect of the invention relates to a seal (26) for sealing a first member, such as a discharge duct (21), to a second member, such as an outer annular shroud, the seal being configured to surround a third turbomachine member, such as...
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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/2021/001615A1 |
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/2020/263395A1 |
A seal assembly (400) in a gas turbine engine (10) is presented. The seal assembly is arranged at a forward side of an inner compressor exit diffuser (222). The seal assembly is arranged between an outlet guide vane assembly (120) and th...
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WO/2020/260810A1 |
The invention relates to an inter-blade platform (20) of a turbomachine fan (1), comprising: - a base (21) comprising a first surface (22) configured to delimit a flow path in the fan (1) and a second surface (23) on the opposite side fr...
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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/2020/256678A2 |
The present invention relates to a brush seal (1) which provides sealing between the high pressure regions and the low pressure regions around the shafts which rotate at high speed and particularly provided in turbo machines like airplan...
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