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Matches 1 - 50 out of 7,619

Document Document Title
WO/2018/146946A1
Provided is a geothermal turbine equipped with a rotor, a casing for housing the rotor, a plurality of moving blades disposed around the rotor, a plurality of stationary blades supported on the casing, and at least one seal part provided...  
WO/2018/146062A1
The invention relates to a guide vane (1) for a turbomachine, having a blade airfoil (2) and at least one platform (3), to which the blade airfoil (2) is connected. A cooling channel system is provided for cooling the platform (3) and th...  
WO/2018/147013A1
Disclosed is a steam turbine which is equipped with a rotor, a casing for housing the rotor, a plurality of moving blades disposed around the rotor, and a plurality of stationary blades supported on the casing, and in which: the stationa...  
WO/2018/145861A1
The invention relates to a sliding ring seal arrangement, comprising a sliding ring seal (2) having a rotating sliding ring (20) and a stationary sliding ring (21), which define a sealing gap (22) therebetween, and an integral safety sea...  
WO/2018/144657A1
This application provides controlled tip balance slits (200) for turbines. An example leakage flow control system (110) for a turbine may include a flow runner (150) with a tip shroud (152), a diaphragm or a guide blade (130), an extensi...  
WO/2018/132246A1
A blade outer air seal with a plurality of inner ring segment secured to a full annular cooled support ring, where the inner ring segments each have rows of curved teeth that form rows of curved grooves that open in a direction toward a ...  
WO/2018/130766A1
The invention relates to a turbine ring assembly comprising a plurality of ring sections (10) consisting of a composite material with a ceramic matrix forming a turbine ring (1) and a ring-supporting structure (3), each section (10) havi...  
WO/2018/131425A1
In order to enhance the efficiency of a gas turbine, this split ring surface-side member is included in a split ring, disposed at a position on the stationary side of the gas turbine and facing a moving blade, and forms a portion of a co...  
WO/2018/128609A1
A turbine rotating component (18) includes an airfoil (20) extending radially from a platform (40). An axial end face (44) of the platform (40) faces a seal gap (50) between the rotating component (18) and a stationary component (12). Th...  
WO/2018/128600A1
A gas turbine engine (10) has a side seal (25a) located between adjacent exit pieces. The side seal (25a) comprises a first seal side (23a) and a second seal side (24a) that contact each other. The first seal side (23a) has a spring (26a...  
WO/2018/114756A1
The invention relates to a seal (1), in particular for high-temperature applications in thermal turbomachines, made of ceramic fiber composite material, wherein the seal (1) has a first section (3a) and a second section (3b), wherein the...  
WO/2018/115456A1
The present invention relates to a method for compressing a gas mixture comprising neon, in a closed-loop cycle. The method comprises: providing a flow of the gas mixture and providing a compression device having at least one gas seal (3...  
WO/2018/110581A1
This gas turbine disassembling/assembling method is configured such that a gas turbine is provided with: a seal plate that is provided to one side in an axial direction with respect to a rotor disk; and a seal plate movement restriction ...  
WO/2018/110476A1
Disclosed is a gas turbine engine (1) that combusts, with a combustor (3), compressed air (CA) compressed by a compressor (2), and drives a turbine (5) by a high-temperature, high-pressure combustion gas (G) which has been generated, the...  
WO/2018/109810A1
This turbine comprises: a balance piston provided to a turbine rotor; a plurality of balance piston seals arranged on a casing side so as to oppose the balance piston; a balance piston bleeding hole that bleeds air from between the plura...  
WO/2018/110584A1
This gas turbine disassembling/assembling method comprises a seal plate restriction state switching step for switching between a seal plate unrestricted state where a seal plate movement restriction part does not restrict radial movement...  
WO/2018/104182A1
The present application provides a turbine (10). The turbine (10) may include a rotor (55), a casing (200), and a gland seal system (100) positioned between the rotor (55) and the casing (25). The gland seal system (100) may include a ba...  
WO/2018/099592A1
The invention relates to a turbocharger having an exhaust-gas-conducting section through which flow can pass, an air-conducting section through which flow can pass, and a bearing section (2) between the exhaust-gas-conducting section and...  
WO/2018/099618A1
The invention relates to a turbocharger, comprising a turbine for expanding a first medium and a compressor for compressing a second medium by using energy obtained in the turbine as the first medium is expanded, wherein the turbine has ...  
WO/2018/101190A1
A high-temperature component (10) for a gas turbine is provided with a main body part (40) and a porous part (42) through which a cooling gas can pass, and is configured such that, in accordance with one or both distributions of a heat l...  
WO/2018/102075A2
An engine or engine casing having an inner annular case and an outer annular case. The engine casing is formed using an additive manufacturing technique such that the inner annular case and outer annular case is formed surrounding a holl...  
WO/2018/095867A1
A rotary machine for acting on a fluid is proposed comprising a stationary housing (2), a rotor (3) for interacting with the fluid, a shaft (4) for rotating the rotor (3) about an axial direction (A), a bearing unit (5) for supporting th...  
WO/2018/096264A1
The invention concerns a method for controlling a control valve (20) of a turbomachine operating at an engine speed at a cruise value (Vc) and oscillating around the cruise value (Vc) of same, the method being implemented by a calculatio...  
WO/2018/091288A1
The invention relates to an assembly for a shroud (28) of an axial turbomachine having a rotor (12), such as a turbomachine compressor air-intake shroud (28). The assembly comprises an annular layer (32) of abradable material that is abl...  
WO/2018/089014A1
A seal assembly (10) arranged to seal a gap between a transition duct (12) of a gas turbine engine and a first stage turbine vane structure (14) is provided. A flexible seal element (26), such as cloth seal, extends between opposed sides...  
WO/2018/082907A1
The invention relates to a sealing segment (11) for forming a sealing ring of a rotor of a gas turbine. The T-shaped sealing segment comprises a central anchoring section (13) that extends circumferentially and radially and has an adjoin...  
WO/2018/082908A1
The invention relates to a sealing segment (11) for forming a sealing ring of a rotor of a gas turbine and to a rotor equipped with corresponding sealing segments (11). The sealing segment (11) comprises a central anchoring section (13) ...  
WO/2018/083403A1
The invention relates to a cooling device (11) for a turbine of a turbomachine extending along an axis, comprising at least one radially inner metal sheet (14) and a radially outer metal sheet (15) that are joined to one another and deli...  
WO/2018/082837A1
The invention relates to a housing arrangement (10) for a turbomachine, comprising an inner housing (12), an outer housing (14) which encloses the inner housing (12) at least partially, and a sealing ring (16) for radial sealing between ...  
WO/2018/085219A1
A flanged component (70) for a gas turbine engine (100) is disclosed herein. The flanged component (70) includes a flange body (79) with a flange mating surface (71) and a plurality of threaded features. Each threaded feature (72) includ...  
WO/2018/080474A1
A liner (10) for a gas turbine engine is inserted into a channel (12) located in a inlet ring (11) of a transition duct (8). The liner is formed as a flat unitary piece with angled ends (14). The angled ends complement each other. When i...  
WO/2018/073210A1
A method of machining a tip (512) profile of a blade (130, 140) for a turbomachine is provided. The method comprises coupling the blade (130, 140) to a component (110, 112, 114, 120, 124) of the turbomachine; supporting the component (11...  
WO/2018/075167A1
A propeller assembly is provided. The propeller assembly includes a central hub including a forward end, an aft end, and a hub body extending therebetween along an axis of rotation of the central hub. The propeller assembly further inclu...  
WO/2018/070282A1
Provided is a labyrinth seal that makes it possible to minimize leakage of a fluid. The labyrinth seal (30) is provided with: an ascending step structure stepped section (41) that is a stepped section on a high pressure side (X1); a desc...  
WO/2018/071018A1
A bimetal thermo mechanical actuator (10) includes a multi-layer bimetal structure (22) that includes a plurality of bimetal structures (12). Each bimetal structure (12) includes a pair of metals, a structural metal (14) and a driving me...  
WO/2018/065739A1
A movable ring assembly (4) for a turbine engine turbine (10) that is mounted between two successive rotor discs (20a) and (20b) of said turbine (10), said rotor discs (20a) and (20b) being fixed to each other by bolting, characterised i...  
WO/2018/048390A1
A flexible seal (10) for at least one component (28) of a turbine engine includes a seal frame (12) with a first end (36) and a second end (38) joined by a first surface (32) and a second surface (34) extending in a longitudinal directio...  
WO/2018/047523A1
Provided is a coating method, a coating film, and a turbine shroud. The present invention includes: a slurry deposition step of depositing a slurry containing a coarsely particulate ceramic and a finely particulate ceramic on a base mate...  
WO/2018/046181A1
The invention relates to an expansion machine (11), comprising a machine housing (20) having a rotatably mounted shaft (21) carrying a rotor (22), wherein a medium is supplied to the rotor (22) during operation, and a rotor (22) having a...  
WO/2018/041555A1
Overall, the invention relates to a seal segment (10) for a turbine and to an assembly for sealing the gaps between seal segments (10) and stator vanes of a turbine. The seal segments comprise a plate-shaped wall (12), the first lateral ...  
WO/2018/042116A1
The invention relates to a device for controlling the clearance between a rotor (1) and a stator (2) surrounding same, which is carried out by modifying the delivery flow carried in a rotor recess (9) in order to provide a bleed flow tha...  
WO/2018/037190A1
Assembly forming a labyrinth seal (1) for a turbomachine, comprising: at least one abradable material (2) of which the inner surface (2i) defines a stair shape with a sequence of treads (4a) and risers (4b); a plurality of fins (3) exten...  
WO/2018/038899A1
A seal (100) for a rotary machine (10) includes a flexible element (124) extending circumferentially about a rotating component (102) and extending generally radially from a first end (128) to a free second end (130). The flexible elemen...  
WO/2018/036818A1
The invention relates to a rotor of a gas turbine, comprising a first rotor disk (01) and a second rotor disk (02), between which a sealing ring formed by sealing segments (31) is arranged. For fastening, according to the invention, the ...  
WO/2018/036696A1
The invention relates to a steam turbine (1), having a turbine housing (2) which has a plurality of turbine housing parts (2a) and surrounds a flow space (3) along a turbine longitudinal axis (4), the turbine housing (2) having a housing...  
WO/2018/034765A1
A drainage system for a stage of a turbine. The drainage system includes at least one annular recess (148) defined in the inner surface (150) of the casing (104) of the turbine and configured to accumulate liquid therein. An axial slot (...  
WO/2018/029957A1
A method for constructing an abradable coating comprises: a slurry layer formation step S2 in which a slurry layer 31 is formed on the surface of a base material 30 using a slurry containing ceramic particles and a solvent; a calcination...  
WO/2018/026757A1
A centrifugal compressor (22, 22' ) includes a casing (30, 30'), a first impeller (34a, 34a', 34b, 34b'), a motor (38), a cooling medium delivery structure (23, 23'), a shaft, (42), and a first bearing (44, 46). The casing (30, 30') has ...  
WO/2018/026579A1
Provided is a method including obtaining ceramic matrix composite (CMC) with a first matrix portion including a silicon carbide and silicon phase dispersed therewithin, disposing a coating thereupon to form a sealed part, and forming the...  
WO/2018/020548A1
A seal structure for a gas turbine rotor blade wherein a shank (12) has a side surface (12a), a side surface (12b), and a bottom surface (12c) that is positioned farther inward in the radial direction than a fin (13). The side surface (1...  

Matches 1 - 50 out of 7,619