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Matches 1 - 50 out of 7,497

Document Document Title
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...  
WO/2018/022314A1
A turbine engine (10) with a stator (118) having axially spaced first (120) and second (122) structural elements along with a rotor (110) and a face seal (100) between the rotor and the stator including a non-rotating gas bearing face (1...  
WO/2018/007717A1
The invention relates to an inserted platform (1) intended for being positioned between two adjacent blades of an aeronautical turbine engine fan, said platform comprising a flow section wall (10) made of composite material including a c...  
WO/2018/003324A1
A clearance measurement method comprising: a first step in which, while moving blades (3) are made to rotate, a sheet-shaped laser light (L) is shone from a light emitting unit (1) having a rotatably supported base end section, from one ...  
WO/2018/004583A1
A stator vane assembly (10) for a gas turbine engine includes a first endwall segment (12) and a second endwall segment (14) arranged circumferentially spaced from each other, whereby a mate face gap (20) is defined between a first mate ...  
WO/2017/220940A1
Disclosed is an annular shroud (10) for a bladed wheel (80), comprising an axially extending annular wall (10A) that has a plurality of axially extending slots (12), each of said slots (12) being designed to accommodate a leading edge (8...  
WO/2017/221771A1
The present invention is able to limit the amount of fluid leakage. A high pressure-side fin (51) is provided on the high pressure-side (X1) of a level difference (40). A low pressure-side fin (52) is provided on the low pressure-side (X...  
WO/2017/221839A1
The present invention pertains to a variable nozzle vane for a variable-capacity turbocharger, wherein: the variable-capacity turbocharger is provided with a scroll flow channel formation part that forms a scroll flow channel toward the ...  
WO/2017/222518A1
A blade and tip shroud assembly for a gas turbine engine. The assembly includes at least one blade with an airfoil extending span-wise along a radial direction. Each blade includes a blade tip. At least one tenon extends radially out fro...  
WO/2017/220282A1
The invention relates to a steam turbine (100, 200), comprising: an inflow housing 109); nozzles (115) fixed in the inflow housing; a rotor (121) having a wheel disk (119) and wheel blades (117), a wheel intermediate space lying between ...  
WO/2017/222630A1
A turbine system including a sealing component is presented. The sealing component includes a ceramic material. The ceramic material includes grains having an average grain size of less than 10 microns. A turbine shroud assembly includin...  
WO/2017/221032A1
A leaf seal assembly 10' is disclosed for use in a gap between a rotating component 1 and a stationary component 2, for example of a turbo-machine. The leaf seal assembly 10 comprises at least one leaf seal 20' having a generally planar ...  
WO/2017/218088A1
A fan assembly is provided. The fan assembly includes a fan, a fan casing circumscribing the fan, and a fan casing heating system in thermal communication with the fan casing. The fan includes a hub, and a plurality of fan blades extendi...  
WO/2017/207890A1
The invention relates to an intermediate turbomachine casing comprising at least a central hub and a shell (12) which are disposed concentrically to one another and connected mechanically by structural arms (11), said casing comprising a...  
WO/2017/209018A1
In order to reduce the amount of leakage of a fluid, this labyrinth seal (30) is equipped with: an increased-diameter step part (41), which is a high-pressure-side (X1) step part; a reduced-diameter step part (42), which is a low-pressur...  
WO/2017/209853A1
A turbine assembly includes a rotor assembly including a shaft coupled to a plurality of rotor stages including a plurality of turbine blades. The shaft and the plurality of turbine blades define a wheelspace therein. The turbine assembl...  
WO/2017/209963A1
Composite fan blade platform includes forward and aft portions and transition portion therebetween. Platform mounting holes extend through increased section thickness in transition portion and conical countersinks centered about centerli...  
WO/2017/203134A1
The invention relates to a method for manufacturing a carrying casing (12) provided with a collar (18) for supporting at least one cartridge of abradable material for a turbomachine, said carrying casing (12) comprising at least one bare...  
WO/2017/203135A1
The invention relates to a method for manufacturing a panel for supporting at least one cartridge of abradable material for a turbine engine casing, said panel including at least one block of honeycomb material covered with a rigid skin,...  
WO/2017/200549A1
A turbine blade tip shroud (22) includes a shroud base (20) extending in a circumferential direction of a turbine engine (64) and further extending in an axial direction of the turbine engine (64) from an upstream edge (56) to a downstre...  
WO/2017/200670A1
The present disclosure is directed to a shroud assembly for a gas turbine engine that includes a first shroud segment, a second shroud segment spaced from the first shroud segment, and a third shroud segment spaced from the first shroud ...  
WO/2017/200656A1
The present disclosure generally relates to variable cellular structures, methods of making such cellular structures, and variable cellular flow discouragers for turbine engines for jet aircraft.  
WO/2017/198916A1
The invention concerns a method for producing a honeycomb structure, comprising the following steps: a) providing a plurality of metal sheets (126) each having, in a first direction, corrugations formed from a succession of crown areas (...  
WO/2017/195575A1
This seal segment (11) is provided with: a retainer (21); a seal body (13) comprising a thin plate seal piece (20); a high pressure-side side plate (23); a low pressure-side side plate; and a block body (50) that comprises a retainer sim...  
WO/2017/194860A1
A turbine ring assembly comprises a plurality of ring sectors (10) made of a ceramic matrix composite material and forming a turbine ring and a ring support structure (3) comprising a first and a second annular flange (32, 36). Each ring...  

Matches 1 - 50 out of 7,497