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公开(公告)号：US12116906B2
公开(公告)日：2024-10-15
申请号：US18269037
申请日：2021-01-06
发明人： Daniel Joo , Ching-Pang Lee , Gm Salam Azad , Sin Chien Siw
CPC分类号： F01D9/06 , F01D25/12 , F05D2220/32 , F05D2240/12 , F05D2260/20
摘要： A turbine vane in a gas turbine engine includes an inner platform, an outer platform, and a vane airfoil positioned therebetween. The vane airfoil includes a first cooling passage extending between the outer platform and the inner platform, and a second cooling passage extending between the outer platform and the inner platform. The second cooling passage is arranged downstream of the first cooling passage with respect to a flow direction. The turbine vane includes a jumper tube disposed between the second cooling passage and the inner platform. The jumper tube includes an inlet, an outlet, and a tube wall enclosing a hollow interior. The inlet is positioned a distance within the second cooling passage. The outlet is positioned at least partially through an aperture of the inner platform.
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公开(公告)号：US12110810B2
公开(公告)日：2024-10-08
申请号：US18158618
申请日：2023-01-24
发明人： Kudum Shinde , Sesha Subramanian , Yashpal Patel
CPC分类号： F01D9/06 , F01D17/105 , F01D17/145 , F02C6/08 , F02C9/18 , F05D2220/323 , F05D2240/14 , F05D2260/232 , F05D2260/605 , F05D2260/606
摘要： A gas turbine engine includes a compressor with an inner casing and an outer casing. The inner casing defines a primary flow path for airflow through the compressor, the inner casing and the outer casing define a bleed air cavity therebetween. The inner casing at least partially defines a first bleed air channel between the primary flow path and the first bleed air cavity. The first bleed air channel is defined between a first wall and a second wall, wherein the first wall is upstream from the second wall. The first wall includes a plurality of holes in fluid communication with the primary flow path and fluidly coupled to a suction manifold. The plurality of holes is configured to energize a fluid boundary layer along the first wall.
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公开(公告)号：US12071855B2
公开(公告)日：2024-08-27
申请号：US17976465
申请日：2022-10-28
发明人： Krzysztof Kowiel
CPC分类号： F01D25/04 , F01D9/065 , F01D25/30 , F16F1/3835 , F16F1/3842 , F05D2230/642 , F05D2250/40 , F05D2260/31 , F05D2260/96 , F16F2224/0225
摘要： An assembly is provided for a gas turbine engine. This engine assembly includes a gas turbine engine case, a conduit and a bushing. The gas turbine engine case includes a case wall and a boss at a port through the case wall. The conduit extends longitudinally along a centerline through the port and into an interior of the gas turbine engine case. The bushing circumscribes the conduit and is arranged within the port. The bushing is engaged with and laterally between the conduit and the boss. The bushing is configured from or otherwise includes a cellular material. The cellular material may be or otherwise include a cellular metal material and/or a cellular composite material.
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公开(公告)号：US12044408B2
公开(公告)日：2024-07-23
申请号：US18344954
申请日：2023-06-30
CPC分类号： F23R3/10 , F01D9/023 , F01D9/04 , F01D9/06 , F02C3/06 , F04D29/544 , F05D2220/32 , F05D2240/35 , F05D2250/13
摘要： A diffuser assembly includes a casing at a compressor aft end; an inner barrel member radially inward of the casing; and an array of radial flow splitters extending between the inner barrel member and the casing. Each radial flow splitter includes a leading edge facing into a flow of air, a trailing end wall opposite the leading edge, a pair of side walls extending between the leading edge and the trailing end wall, and an axis extending through the leading edge and the trailing end wall. A width of each radial flow splitter increases from the leading edge to the trailing end wall. The side walls diverge away from the axis in a downstream direction corresponding to the flow of air. Optionally, the side walls also diverge away from the axis in a radial direction between the inner barrel member and the casing.
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公开(公告)号：US12044149B2
公开(公告)日：2024-07-23
申请号：US18333443
申请日：2023-06-12
发明人： Marc J. Muldoon
摘要： A cooling system for a plurality of conductive cables in a gas turbine engine includes a cooling source and an electric motor disposed in a tail cone. The cooling source may comprise an electric fan or an oil pump. The cooling source may be configured for active cooling of the plurality of conductive cables. The electric fan may be in fluid communication with ambient air during operation of the gas turbine engine.
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公开(公告)号：US20240229664A1
公开(公告)日：2024-07-11
申请号：US18152904
申请日：2023-01-11
CPC分类号： F01D9/065 , F01D9/041 , F02C6/08 , F05D2220/3218 , F05D2240/121 , F05D2240/122 , F05D2260/606
摘要： A gas turbine engine includes a compressor section having rotor shaft assembly and a stator shroud assembly including a stator shroud casing surrounding the compressor rotor shaft assembly, a compressor flow passage being defined between the compressor rotor shaft assembly and the stator shroud casing. A compressor bleed air system includes a compressor bleed air duct that includes a sloped inlet portion, such as a NACA submerged inlet portion, in the stator shroud casing. Alternatively, stator vanes at a compressor bleed air passage may have a NACA inlet scoop and an airflow passage through the stator vane providing a bleed airflow to a cavity, which has airflow passages providing bleed air to an upstream side of the bleed air passage.
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公开(公告)号：US12012872B1
公开(公告)日：2024-06-18
申请号：US18180245
申请日：2023-03-08
发明人： Philippe Savard , Guy Lefebvre , Remy Synnott
CPC分类号： F01D9/065 , F01D25/16 , F01D25/18 , F01D25/24 , F01D25/28 , F05D2220/323 , F05D2230/72 , F05D2250/232 , F05D2250/63 , F05D2260/31 , F05D2260/98 , F01D25/28 , F01D9/065
摘要： A service tube assembly, has: a service tube having a threaded end portion and an outer shoulder adjacent to the threaded end portion, the outer shoulder having a frustoconical shoulder face converging towards the tube axis and away from the threaded end portion; a mating part threadingly engaged by the threaded end portion, the mating part having a seat face converging towards the service tube and towards the threaded end portion; a locking member extending from a first end to a second end, the first end including a notch receiving the outer shoulder, the notch circumscribed by a frustoconical notch face abutting the frustoconical shoulder face to create a frustoconical-to-frustoconical contact surface between the locking member and the outer shoulder, the second end in abutment against the seat face; and a mechanical fastener releasably holding the locking member in abutment against both of the outer shoulder and the mating part.
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公开(公告)号：US20240175371A1
公开(公告)日：2024-05-30
申请号：US18071182
申请日：2022-11-29
发明人： Ted J. Freeman , Aaron D. Sippel
CPC分类号： F01D11/08 , F01D9/06 , F01D25/246 , F05D2240/14 , F05D2260/201 , F05D2300/6033
摘要： A turbine shroud assembly for use with a gas turbine engine includes a blade track assembly and a carrier assembly. The blade track assembly includes a blade track segment made of ceramic matrix composite materials and arranged to define a portion of a path of the turbine shroud assembly. The carrier assembly includes a carrier segment made of metallic materials that supports the blade track segment to locate the blade track segment radially outward of the axis.
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公开(公告)号：US11920495B1
公开(公告)日：2024-03-05
申请号：US18099610
申请日：2023-01-20
CPC分类号： F01D5/147 , F01D5/188 , F01D5/282 , F01D5/284 , F01D5/187 , F01D9/065 , F05D2240/304 , F05D2260/2214 , F05D2300/6033 , F05D2300/6034
摘要： An airfoil includes an airfoil wall that has a wishbone-shaped fiber layup structure. The structure includes two arms that merge into a single leg. The single leg includes fiber tows from each of the arms that are interwoven. The single leg forms at least a portion of the trailing edge of the airfoil wall. Each of the arms includes a first section that is distal from the single leg and a second section that is proximal to the single leg. The first section defines a first thickness, the second section defines a second thickness that is greater than the first thickness, and the single leg defines a third thickness that is greater than the second thickness.
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公开(公告)号：US11795828B2
公开(公告)日：2023-10-24
申请号：US17594071
申请日：2020-03-16
发明人： Matthieu Simon , Jean-Luc Bacha , Paul Danre , Léandre Ostino
CPC分类号： F01D5/189 , F01D9/065 , F05D2230/237 , F05D2240/30 , F05D2260/201
摘要： A blade for a turbomachine intended to be disposed about an axis while extending radially between a radially outer end and a radially inner end, the blade having at least one cooling cavity opening out to the radially outer end of the blade and to the radially inner end of the blade, the blade having at least a first tubular liner and at least a second tubular liner each engaged in the cavity, the radially outer end of the first liner opening out to the radially outer end of the blade, and the radially inner end of the second liner opening out to the radially inner end of the blade.
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