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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...
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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...
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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...
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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...
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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 ...
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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...
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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...
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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...
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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 ...
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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...
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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 (...
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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...
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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 ...
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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...
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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...
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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...
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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...
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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 ...
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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 ...
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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...
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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...
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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 ...
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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...
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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 ...
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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...
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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 ...
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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...
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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...
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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...
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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...
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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...
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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...
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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,...
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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...
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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 ...
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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.
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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 (...
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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...
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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...
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WO/2017/195550A1 |
This seal segment (11) is provided with: a seal body comprising a plurality of layered thin plate seal pieces (20); and a high pressure-side side plate (23). The high pressure-side side plate (23) comprises: an outer diameter-side edge (...
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WO/2017/196563A1 |
An aspirating face seal between high and low pressure regions of a turbomachine at a juncture between rotatable and non-rotatable members of turbomachine includes gas bearing rotatable and non-rotatable face surfaces. Starter seal tooth ...
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WO/2017/195704A1 |
A seal segment (11) is provided with: a retainer that extends on the outer circumferential side of a rotating shaft in the circumferential direction (Dc) of the rotating shaft; a first seal body (13) that extends inward in the radial dir...
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WO/2017/191071A1 |
A system for cooling a blade (38) in a rotor (22) of a gas turbine (10), the blade (38) comprising: - a root (122) for connecting the blade (38) to the rotor (22), - an aerofoil (126) connected to the root (122), - a cooling passage exte...
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WO/2017/182740A1 |
The invention relates to a device (2) for cooling a turbine casing, preferably of a low-pressure turbine of a turbomachine, with air jets, the device comprising a pressurised air supply housing (3) and at least two curved cooling pipes (...
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WO/2017/178203A1 |
The present invention relates to a turbine blade (10) for a turbomachine, comprising a blade airfoil (1) with a blade tip region (3) and a sealing region (2) which has an auxetic material and is arranged and designed such that, when tran...
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WO/2017/178747A1 |
The invention relates to a blade (16), in particular a fan blade, for resurfacing an abradable coating (26) on an internal surface of a turbine engine case (18) intended to surround the blade. The comprises a root (20) and an airfoil (24...
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WO/2017/180682A1 |
An aspirating face seal between high and low pressure regions of a turbomachine at a juncture between rotatable and non-rotatable members of turbomachine includes gas bearing rotatable and non-rotatable face surfaces. Primary and starter...
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WO/2017/174278A1 |
The invention relates to a guard device (8) comprising an enclosure (10) for enclosing a first machine (4), a coupling guard (12) for covering a coupling device (20) that is prepared for connecting the first machine (4) to a second machi...
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WO/2017/177229A1 |
A turbomachine sealing component has: a substrate having circumferential surface; and a coating on the circumferential surface. The coating or a layer thereof is patterned to form circumferential sealing ridges.
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WO/2017/167615A1 |
The invention relates to a turbine blade (100) comprising: a blade tip, a cooling structure (10) comprising cooling channels (5) which are designed to have cooling fluid passed through them in order to cool the turbine blade (100) during...
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