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Patent Searching and Data


Matches 1 - 50 out of 7,381

Document Document Title
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...  
WO/2017/154257A1
Tapered surface sections 21f, 22f are formed on inner-side surfaces of base sections 21a, 22a facing a flow path 14 at an outer band part 21 and an inner band part 22 of one of turbine stator blades 11, said turbine stator blades 11 bein...  
WO/2017/155497A1
A turbine blade (10) includes an airfoil (12) extending span-wise along a radial direction (Ra) relative to a turbine axis having a leading edge (14) and a trailing edge (16) joined by a pressures side (18) and a suction side (20), a tip...  
WO/2017/149263A1
A rotary seal assembly (2) comprises first and second sealing elements configured for rotational relative movement about a rotational axis and providing a sealing interface between adjacent first and second sealing faces of the first and...  
WO/2017/151146A1
An air cooled turbine stator vane with an impingement cooling insert (12,13) secured within a cavity, where a forward and an aft seal slot are formed between a backside surface of an airfoil and the impingement cooling insert in which fl...  
WO/2017/148891A1
In a gas turbine system (10) having a turbine (12) which can be impinged on by hot gas and which has a turbine wheel (18), having a combustion chamber (14) for generating hot gas for the turbine (12) and having a compressor (24) with a c...  
WO/2017/148630A1
The invention relates to a rotor (01) for use in a gas turbine, comprising a plurality of compressor segments (21), a plurality of central segments (31), and a plurality of turbine segments (41); the compressor segments (21) and the turb...  
WO/2017/150365A1
Provided are a seal structure and a turbomachine designed so as to be capable of effectively minimizing unstable vibrations. This seal structure minimizes the flow of a working fluid leak (SL) from a gap (Gd) between a rotating structure...  
WO/2017/144801A1
The invention relates to a device (11) for applying abradable material to a surface of an annular casing (1) of a turbomachine, the casing extending along a longitudinal axis, the device (11) comprising a support (12, 13) provided with f...  
WO/2017/145623A1
An insert assembly (79) equipped with an insert (80), a reinforcing member (85), and a holding member (90). The insert (80) is affixed to one end of a blade main body (51) in the radial direction. The reinforcing member (85) is arranged ...  
WO/2017/140985A1
The invention relates to a turbine shroud sector (10) made of ceramic matrix composite material having a portion forming an annular base (12) with an inner surface intended for defining the inner surface of a turbine ring (1) when the sh...  
WO/2017/142077A1
This rotary machine is provided with a stationary body having a stationary-side primary surface (13) and a rotating body having a rotation-side primary surface (54) facing the stationary-side primary surface (13). One among the stationar...  
WO/2017/141929A1
Provided is a brush seal with which there is little leakage of a sealed fluid. This brush seal is provided with a brush (4) having a plurality of bundled bristles, and an annular back plate (2) disposed on a low-pressure side of the brus...  
WO/2017/142011A1
A sealing device (50) according to the present invention seals a gap between the outer peripheral surface of a rotor and the inner peripheral surface of a stator, and is provided with: a sealing ring (51) which is provided to the stator ...  
WO/2017/142572A1
A ceramic matrix composite ("CMC") component, such as a turbine blade (80) for a combustion turbine engine (20) that has a fiber-reinforced, solidified ceramic substrate (88). The substrate (88) has an inner layer of fibers (100), for en...  
WO/2017/138795A1
The present invention relates to a power generation cycle system comprising: a pump module for allowing working fluid to flow; a first heat exchange module for receiving the working fluid from the rear end of the pump module and heating ...  
WO/2017/134976A1
A method for implementing an abradable coating comprising: a pattern-forming step S1 in which, using a slurry containing ceramic particles and solvent, a slurry pattern is formed on the surface of a thermal barrier coating layer; and a f...  

Matches 1 - 50 out of 7,381