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Matches 1 - 50 out of 7,441

Document Document Title
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...  
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 (...  
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 ...  
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...  
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...  
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 (...  
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...  
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...  
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...  
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...  
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.  
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...  
WO/2017/162975A1
The invention relates to a platform (30) to be inserted between two adjacent blades (20) of a fan (2), and comprising a flow passage wall (34), a base wall (36), and axial and radial retaining surfaces. The flow passage wall (34) defines...  
WO/2017/164884A1
A gas turbine engine has an outer ring (15) formed by integrated exit pieces (10) and surrounds an inner ring (16). A seal section (20) having an L-shaped cross-section is positioned in a respective slot (11, 12) in the outer and inner r...  
WO/2017/165261A1
The invention relates to an oil sealing unit for a turbocharger used for sealing a passage from a bearing housing to a compressor housing having an end wall, wherein the end wall serves to delimit an oil expansion chamber in the directio...  
WO/2017/163911A1
This rotary machine (100) is equipped with: a rotor (1) on the outer circumferential surface (1S) of which recesses (8) are formed; stator blades (7) each having a stator blade body (70) extending from the outside toward the inside in th...  
WO/2017/159770A1
The present invention provides an optical measurement device, an optical measurement method, and a rotating machine with which it is possible to eliminate errors caused by thermal elongation and centrifugal elongation. The present invent...  
WO/2017/158637A1
A turbine equipped with a cylindrical casing and turbine stator blades arranged along the circumferential direction in the interior of the casing, said turbine blades having: a blade effective section; a cooling medium flow path for circ...  
WO/2017/159768A1
Provided is an optical measurement device, an optical measurement method, and a rotary machine, wherein protection is provided for optical sensors and degradation of S/N ratio is prevented. Thus, this optical measurement device equipped ...  
WO/2017/158264A1
The invention relates to a method for manufacturing a turbine shroud (24) for a turbomachine, involving manufacturing at least one turbine shroud segment (26), placing the turbine shroud segment (26) in a lower mold in such a way that an...  
WO/2017/158265A1
The invention relates to a method for manufacturing an abradable plate (32) for a turbine shroud (24, 26) of a turbomachine, said method involving preparing a mixture comprising a cobalt- or nickel-based metal powder and a powder based o...  
WO/2017/158266A1
The invention relates to a stator ring (20) of a flow path, preferably secondary, of a turbomachine (1), said ring (20) comprising: – an inner platform (52, 56) and an outer platform (54), – a plurality of stators (40) extending radi...  
WO/2017/153219A1
The invention relates to a rotor blade for a gas turbine, comprising a blade (1) extending in a radial direction, with a blade body (2) comprising a periperal wall with a pressure-side wall section (3a) and a suction-side wall section (3...  

Matches 1 - 50 out of 7,441