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Patent Searching and Data


Matches 1 - 50 out of 7,754

Document Document Title
WO/2019/115999A1
Apparatus and methods for measuring clearance are disclosed. In one arrangement, a sensor is used to output a signal that is dependent on a separation between the component and the reference structure. A passage event integration compris...  
WO/2019/110210A1
A heat shield (60) for a gas turbine engine (10), the heat shield (10) comprising a main body (61) having a first surface (70) and a second surface (72), the first surface (70) being exposed to a hot working gas in use, a plurality of wa...  
WO/2019/110934A1
Coating with property gradient intended to be affixed by additive manufacturing to an inner wall of a housing (46) mounted at the periphery of mobile rotor blades of a turbomachine, the coating comprising, as superposed layers, from an o...  
WO/2019/106286A1
The invention relates to a method for measuring the flow rate of cooling air in a cooling air circuit (13) of a casing (121) of a high-pressure turbine (9) of a turbomachine (1). The invention is characterized in that sensors (21, 22, 24...  
WO/2019/106024A1
A seal segment (128) for a machine (100) includes a circumferentially extending stationary seal body (200) configured to be coupled to a casing (110) of the machine, and a support member (204) extending radially inward from the stationar...  
WO/2019/102124A1
An abradable structure (36) is provided, with regions (44, 45, 46) with lower resistance to wearing produced by labyrinth seal lips (4, 5), at specific points in the axial direction of the turbomachine, where lip interference could cause...  
WO/2019/097058A1
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 (143) lying b...  
WO/2019/097905A1
This annular seal for a gas turbine is provided with: a first part extending in the circumferential direction on one end side in the axial direction and comprising a first groove opening on the one end side in the axial direction; and a ...  
WO/2019/097286A1
A labyrinth seal lip (5) comprises, standing on one of its lateral faces (7), a deflector (13) which channels the flow of gas tangent to the lip (5) towards the facing seal (4) so as to disturb the leakage flow (22) through the gap and d...  
WO/2019/099009A1
A clearance control system for controlling a clearance between rotating blades and a boundary adjacent to tips of the rotating blades is provided. Electrical heating circuitry (62) may be embedded within or otherwise disposed onto a vane...  
WO/2019/083475A2
The invention relates to the construction of a woven cloth layer (3) designed in a way that it will be placed between metal sheets (2) in order to support them in the sealing element (1) which is mounted to provide sealing around the rot...  
WO/2019/082737A1
This axial-flow fluid machine is provided with: a holding ring (30) holding a stationary blade train; a casing (20) supporting the holding ring (30); and an eccentric pin (80). An engagement part (23) of the casing (20) has a protruding ...  
WO/2019/081861A1
The invention relates to a retention device (101) for at least one cooling tube (120) of a cooling system (100) for a turbomachine case (10), the case (10) extending about an axial direction (X) of the turbomachine, the retention device ...  
WO/2019/077251A1
Aircraft turbomachine (100) comprising a first channel (200) enabling communication between a high pressure compressor (30) and a high pressure turbine (50), a second channel (400) enabling communication between the high pressure compres...  
WO/2019/074389A1
The present invention provides a micro compressor seal arrangement to minimize a working medium flow from a high pressure area to a low pressure area through a gap is presented. The micro compressor seal arrangement comprises a rotor ...  
WO/2019/075283A1
A thrust bearing assembly for a turbocharger includes a first thrust portion (50) disposed on a turbocharger shaft of the turbocharger, a second thrust portion ( 52) disposed on the turbocharger shaft and spaced axially from the first th...  
WO/2019/063909A1
A turbomachine rotor blade comprising a radially outer end equipped with a heel, the heel being provided with at least one sealing wiper (3), the or each sealing wiper (3) projecting beyond the heel along a first axis (z), the first axis...  
WO/2018/160270A3
A system and method (90) for monitoring a gap size of a gap (38) between a seal holder (28) and an adjacent disk (14) in a compressor section (10) of a gas turbine. An imaging device (50) is used to generate at least one image of the gap...  
WO/2019/058046A1
A method for manufacturing a part made from CMC, i.e. ceramic matrix composite material, provided with at least one cutout, and such a part made from CMC provided with at least one cutout, the method comprising the following steps: provi...  
WO/2019/059273A1
A rotating machine (1) control device (100) is provided with: an operating terminal (36) for changing a parameter of the rotating machine (1); a clearance measuring device (101) which measures the amount of clearance between a rotor (41)...  
WO/2019/053095A1
The invention relates to a sealing ring (1) for sealing an annular gap between a shaft and a bearing body surrounding said shaft, comprising two sealing ring halves (2, 3) having ring segment shapes and a plurality of circumferentially f...  
WO/2019/049873A1
A variable nozzle turbocharger 1 comprising: nozzle rings 21, 22 that define a scroll flow path 23; a variable nozzle 30 arranged in the scroll flow path; and a nozzle shaft 40. In the variable nozzle turbocharger having the nozzle shaft...  
WO/2019/048766A1
The invention relates to a turbine assembly (1) comprising an annular structure extending circumferentially about an axial direction (DA) and comprising ring segments (10) arranged circumferentially end to end and comprising adjacent con...  
WO/2019/049870A1
A variable nozzle turbocharger 1 comprising: nozzle rings 21, 22 that define a scroll flow path 23; a variable nozzle 30 arranged in the scroll flow path; and a nozzle shaft 40. In the variable nozzle turbocharger having the nozzle shaft...  
WO/2019/050679A1
A compressor system (10) includes a gas compressor (18) with dry gas seals (66, 68) about a driveshaft (64). The compressor system (10) also includes a fugitive gas system (30) having a gas conduit (36) in fluid communication with a coll...  
WO/2019/045590A1
The present invention provides a pressure actuated seal arrangement (1) to regulate flow of a working medium flow from a high pressure area (2) to a low pressure area (3) through a gap (6) is presented. The pressure actuated seal arrange...  
WO/2019/040079A1
Processes and systems are described herein which 3D print a ceramic fiber composite (24, 48) in a printed pattern (308) and deposit a thermal barrier coating (318) over the printed pattern (308) to define a three-dimensional abradable su...  
WO/2019/040291A1
A seal arrangement for a turbine stage includes a vane assembly including a radially inner vane platform (12), a radially outer vane platform (30), and an airfoil (28). The seal arrangement further includes a rim seal feature (14) includ...  
WO/2019/040171A1
The present invention is related to a seal plate assembly (300) for a rotor disk assembly (100) of a gas turbine engine, wherein the seal plate assembly includes a plurality of adjacent seal plate segments (320, 340). Shiplaps (322,323,3...  
WO/2019/035178A1
Provided is a turbine stationary blade row provided with: stationary blades (31) each having a blade effective portion (40), an outer ring side wall (50) provided on the outer circumferential side of the blade effective portion (40), an ...  
WO/2019/030314A1
A component (300, 400) for use in a turbomachine is provided. The component (300, 400) comprises a platform (310, 410) having a leading end (312, 412) longitudinally spaced apart from a trailing end (312, 412), an aerofoil portion (320, ...  
WO/2019/028208A1
A turbine component (1) such as a blade or vane includes at least one platform (6) provided with a platform cooling circuit (30). The platform cooling circuit (30) includes an inlet (32) for receiving a coolant (K), and a cooling channel...  
WO/2019/025093A1
The invention relates to a method for producing a sealing element for sealing a flow path in a gas turbine having a lattice structure (1), the lattice structure (1) being generated by an additive method of manufacture. The invention furt...  
WO/2019/013178A1
The purpose of the present invention is to reduce a loss in motion energy causing rotor blades rotate, the loss being due to interference between a leakage flow at the distal end of the rotor blade and a main flow causing the rotor blade...  
WO/2019/013664A1
A labyrinth sealing arrangement including a first part, a second part, and an axial series of seal fins is presented for rotating equipment such as a gas turbine. The first and the second parts are relatively rotatable within the rota...  
WO/2019/013665A1
The present invention provides a seal arrangement to minimize flow of a working medium from a high pressure area to a low pressure area is presented. The seal arrangement comprises a first part and a second part, wherein the first par...  
WO/2019/007907A1
The sealing system (1) for a machine comprises: a sealing element (4) that is movable back and forth along a direction (D) and that comprises a first recess (41) with first and second surfaces (42, 43), a component (2) of an assembly of ...  
WO/2019/009886A1
A gas turbine sealing interface (10) to seal (30) a gap between a transition duct (12) and a turbine section component is provided. The transition duct (12) includes an outlet exit frame (12, 14) including at least one fastener hole (18)...  
WO/2018/236510A1
A plurality of ring segments (35) of a ceramic matrix composite material are used to create a ring seal (34). Each ring segment (35) is formed from three circumferentially extending rails (41, 42, 43) that are placed adjacent one another...  
WO/2018/233903A1
The invention relates to a method for checking a steam turbine, wherein a first operating variable (1) and a second operating variable (2) are determined, wherein a correlation between the first (1) and second (2) operating variable prev...  
WO/2018/235857A1
A variable nozzle unit is provided with: a plurality of movable nozzle vanes each including a nozzle body which includes a blade portion arranged in a gas inflow passageway of a turbine, and a nozzle shaft protruding from the nozzle body...  
WO/2018/229385A1
The invention relates to a device (26) for cooling an annular outer turbine casing (17), the device (26) comprising at least one circumferentially extending tube (27) having an air inlet and intended for conveying cooling air, said tube ...  
WO/2018/230411A1
An axial flow rotating machine is provided with: a rotor (20); a plurality of stator vanes (42); and a medium flow modification member (60). The stator vanes (42) include an inner shroud (44) and one or more seal fins (49). A rotor shaft...  
WO/2018/212073A1
This gas turbine has: a plurality of first cooling channels (61) that have a plurality of blade rings (50) disposed radially outward thereof where a rotational shaft serves as the center, and that extend in the axial direction and are di...  
WO/2018/206306A1
The invention relates to a method for maintaining an axial-flow turbomachine (1), which has a support structure (2) and a plurality of axially adjacent guide vane rings (3, 4, 5) each of which has a plurality of guide vanes (6), each gui...  
WO/2018/207754A1
This turbine housing (10) is provided with: an inner cylinder (20) forming a discharge gas flow passage (K) between a discharge gas inlet-side flange (12) and a discharge gas outlet-side flange (13); and an outer cylinder (40) covering t...  
WO/2018/203892A1
A circumferential seal assembly (30) for use between a higher pressure side (36) and a lower pressure side (37) is presented. The seal assembly (30) includes a primary sealing ring (31), a second sealing ring (32), a third sealing ring (...  
WO/2018/203924A1
A rim seal for a turbine in a gas turbine engine, the rim seal formed between a rotor and a stator of the turbine and includes a first seal with an expansion cavity and a second seal formed radially inward of the first seal. A buffer cav...  
WO/2018/195838A1
Provided is an impeller turbine assembly, comprising a rotating shaft (3), with one end of the rotating shaft (3) being installed with an impeller (1), and the other end thereof being installed with a turbine (4), wherein the impeller (1...  
WO/2018/197800A1
The invention relates to a sealing device for use between a rotor part and a stator part, comprising at least one abradable coating (46) interacting with at least two upstream and downstream rubbing strips. Axially upstream of the rubbin...  

Matches 1 - 50 out of 7,754