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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)...
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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...
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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...
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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...
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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...
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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...
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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...
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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...
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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...
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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...
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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 ...
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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, ...
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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...
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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...
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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...
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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...
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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...
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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 ...
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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)...
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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...
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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...
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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...
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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 ...
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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...
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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...
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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...
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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...
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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 (...
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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...
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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...
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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...
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WO/2018/197114A1 |
The invention relates to a ceramic sealing system between a rotor blade (120) and a housing (1''). By means of the combination of a small porous zirconium oxide layer (11) on a turbine rotor blade, which zirconium oxide layer faces a cer...
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WO/2018/200636A1 |
A variable turbine geometry (VTG) turbocharger is disclosed. The VTG turbocharger may comprise a turbine section having a turbine wheel and plurality of guide vanes configured to regulate a flow of exhaust gases to the turbine wheel. The...
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WO/2018/195122A1 |
This disclosure relates to various seals for sealing around exhaust pipes, such as the exhaust pipe of an aircraft auxiliary power unit. The seal can include a collar portion bounding an opening that is configured to receive the exhaust ...
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WO/2018/192846A1 |
The invention relates to a shaft seal (2) for sealing a shaft gap (5) between a shaft (3) and another machine component, comprising a plurality of sealing segments (4) that can be arranged around the shaft (3) in a peripheral direction (...
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WO/2018/189176A1 |
The invention relates to a power plant (1) comprising a steam turbine (2) with a shaft (3), further comprising a condenser (4) mounted downstream of the steam turbine (2) in the direction of flow of the steam, a vacuum pump (5) mounted d...
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WO/2018/191214A1 |
A variable turbine geometry (VTG) turbocharger is disclosed. The VTG turbocharger may comprise a turbine section, a bearing section, and an actuation pivot shaft (APS) having a bearing side in the bearing section and a pressure side in t...
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WO/2018/190932A2 |
A shroud assembly for a turbine engine comprising a plurality of circumferentially arranged shroud segments having confronting end faces defining first and second radially spaced surfaces. The shroud assembly includes a forward edge span...
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WO/2018/188874A1 |
The invention relates to a sealing component (6), in particular for sealing a vapor chamber with respect to the surroundings or two vapor chambers having different pressures, comprising at least one ring- or ring-segment-shaped main body...
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WO/2018/184788A1 |
The invention relates to a method for sealing an annular gap (11) in a turbine with a housing (1) and a rotor (2), which is arranged in the housing (1), is mounted to rotate about its central longitudinal axis, and is equipped with a plu...
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WO/2018/177864A1 |
The invention relates to a turbocharger (1) for an internal combustion engine, comprising - a bearing housing (41), in which a rotor shaft (14) is mounted rotatably about a rotor axis of rotation (15); - an exhaust gas turbine (20) havin...
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WO/2018/181331A1 |
This drain removing device (20) for a steam turbine (1) is provided with: a first annular part (30) which extends in the axial direction from an outer ring part (8) holding a stationary blade (4) and extends in the circumferential direct...
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WO/2018/173316A1 |
This shaft seal device (1A) is provided with a seal ring and a thin-plate seal (25). The seal ring comprises a plurality of seal segments (20A) provided in the circumferential direction such that end surfaces (21s) in the circumferential...
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WO/2018/173315A1 |
This shaft seal device (1) is provided between a rotor and a stator surrounding the rotor, and partitions a space between the rotor and the stator into a high-pressure region (S2) and a low-pressure region in the direction (Da) of the ce...
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WO/2018/175356A1 |
The invention is related to a bladed rotor system (10) for a turbomachine including blades (14) mounted circumferentially on a rotor disc (12), and a plurality of under-platform dampers (30). Each damper (30) is located between adjacent ...
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WO/2018/172653A1 |
A turbine ring assembly comprising ring sections (10) forming a turbine ring (1) and a ring support structure (3), each ring section (10) having, along a section plane defined by an axial direction (DA) and a radial direction (DR) of the...
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WO/2018/172654A1 |
A turbine ring assembly comprising ring sectors (10) forming a turbine ring (1) and a ring support structure (3), each ring sector (10) having, in a plane of section defined by an axial direction (DA) and a radial direction (DR) of the r...
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WO/2018/174739A1 |
A system provides mobility of a stator shroud (7) in a turbine stage (1). Said turbine stage comprises a plurality of blades (4) that are connected to a rotor disc (3), a stator (6), and at least one stator shroud that comprises a plural...
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WO/2018/172655A1 |
A turbine ring assembly comprising ring sections (10) forming a turbine ring (1) and a ring support structure (3), each ring section (10) having, along a section plane defined by an axial direction (DA) and a radial direction (DR) of the...
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WO/2018/157957A1 |
The invention relates to a turbine casing (1) for a turbine, in particular a steam turbine, having a front casing segment (3), which is formed around a turbine longitudinal axis (2) and has a first front casing part-segment (3a) and a se...
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