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公开(公告)号：US20240352864A1
公开(公告)日：2024-10-24
申请号：US18357301
申请日：2023-07-24
CPC分类号： F01D11/08 , F01D25/16 , F05D2220/32 , F05D2240/50 , F05D2240/55
摘要： A turbine engine includes a rotor, a stator having a carrier, and a seal assembly that is disposed between the rotor and the stator. The seal assembly includes a plurality of seal segments. The plurality of seal segments includes a seal segment having a seal face forming a fluid bearing with the rotor, a body, and an aft bearing extending from the body. The turbine engine further includes a roller assembly having one or more rolling elements coupled to one of the aft bearing or the carrier. The one or more rolling elements in rolling contact with the other of the aft bearing or the carrier.
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公开(公告)号：US12110798B1
公开(公告)日：2024-10-08
申请号：US18428956
申请日：2024-01-31
申请人： RTX CORPORATION
CPC分类号： F01D11/08 , F01D11/122 , F05D2220/32 , F05D2230/22 , F05D2230/312 , F05D2230/90 , F05D2240/11 , F05D2300/6033
摘要： A gas turbine engine includes a compressor section, a combustor section and a turbine section for rotation on an axis. The turbine section includes at least one row of rotating turbine blades each having a radially outer tip. A blade outer air seal is positioned radially outwardly of the radially outer tip. The blade outer air seal has a central web positioned radially outwardly of the radially outer tip. The blade outer air seal has an upstream mount arm and a downstream mount arm receiving mount structure from a static structure. The static structure has sealing members engaging an upstream outer surface of the upstream mount arm at an upstream seal material and a downstream outer surface of the downstream mount arm at a downstream seal material. A method is also disclosed.
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公开(公告)号：US20240318572A1
公开(公告)日：2024-09-26
申请号：US18189424
申请日：2023-03-24
发明人： Narendra Anand Hardikar , David Raju Yamarthi , Rahul Anil Bidkar , Ravindra Shankar Ganiger , Prateek Jalan , Deepak Trivedi
IPC分类号： F01D11/08
CPC分类号： F01D11/08 , F05D2220/30 , F05D2230/60
摘要： A turbine engine is provided. The turbine engine defines a radial direction and includes: a rotor; a stator comprising a carrier; a seal assembly disposed between the rotor and the stator, the seal assembly comprising a first seal segment, the seal segment having a seal face configured to form a fluid bearing with the rotor; and a seal support assembly, the seal support assembly comprising a prestressed spring assembly extending from the seal segment for biasing the seal segment along the radial direction.
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公开(公告)号：US12078076B2
公开(公告)日：2024-09-03
申请号：US18338449
申请日：2023-06-21
发明人： Yun Chang Jang , Simon Hauswirth , Richard Jones
CPC分类号： F01D25/14 , F01D9/04 , F01D9/041 , F01D11/08 , F01D25/12 , F05D2240/11 , F05D2260/201 , F05D2260/232
摘要： A ring segment and a turbomachine including the ring segment are provided. The ring segment installed on an inner circumferential surface of a casing and disposed to face an end of a blade existing inside the casing, the ring segment includes a segment body disposed inside the casing in a radial direction of the casing and having a channel through which cooling air flows, and a pair of segment protrusions protruding outward from the segment body, coupled to the inner circumferential surface of the casing, and spaced apart from each other along a flow direction of fluid flowing through the casing to form an RS cavity through which cooling air flows, wherein the segment body includes a cavity for supplying cooling air introduced from the RS cavity to the channel.
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公开(公告)号：US12044132B1
公开(公告)日：2024-07-23
申请号：US18195159
申请日：2023-05-09
发明人： Jonas Banhos , James T. Roach , Russell Kim
CPC分类号： F01D11/08 , F01D25/14 , F05D2240/55 , F05D2260/2214 , F05D2300/6033
摘要： A seal arc segment includes a wall that defines radially inner and outer sides, forward and aft ends, and first and second circumferential sides. The wall includes a CMC ply lay-up of a radially inner-most CMC ply on the inner side, a radially outer-most CMC ply on the radially outer side, and radially intermediate CMC plies therebetween. At least one of the radially intermediate CMC plies has cutout voids that define cooling channels in the wall. The cooling channels are bound on lateral channel sides by the at least one of the radially intermediate CMC plies, bound on a radially inner channel side by a first adjacent one of the CMC plies, and bound on a radially outer channel side by a second, different adjacent one of the CMC plies. The radially outer-most CMC ply includes at least one inlet hole connected to the cooling channels for providing cooling air.
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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：US20240110487A1
公开(公告)日：2024-04-04
申请号：US18477912
申请日：2023-09-29
申请人： RTX CORPORATION
发明人： Daniel S. Rogers , James E. Weisheit , Morely S. Sherman , Mikayla M. Rogers , Timothy J. Harding , Marshall F. Thayer , Joseph Micucci
CPC分类号： F01D11/08 , F01D9/04 , F05D2300/6033
摘要： A gas turbine engine includes a turbine section that has a retainer ring, a first vane that bears against the retainer ring to prevent movement of the first vane in a first axial direction, a second vane axially spaced from the first vane, and a blade axially between the first vane and the second vane. A blade outer air seal is situated radially outwardly of the blade. The blade outer air seal includes a ceramic matrix composite body that defines a core gaspath side that faces the blade, a forward end, an aft end, and circumferential sides. There is a spring seal at the aft end of the blade outer air seal that seals against the second vane. The spring seal provides a preload that biases the blade outer air seal against the first vane and thereby biases the first vane against the retainer ring.
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公开(公告)号：US11905838B2
公开(公告)日：2024-02-20
申请号：US17628636
申请日：2020-07-16
发明人： Tatsuro Furusho , Shin Nishimoto , Hidekazu Uehara , Kohei Ozaki , Azumi Yoshida
摘要： A seal member is disposed between a rotor and a stator to provide a seal between the rotor and the stator. The seal member comprises: a rotary-side member fixed to a surface of the rotor opposing the stator; a fixed-side member fixed to the stator and facing the rotary-side member; and a first fin and a second fin which are disposed on one of the rotary-side member and the fixed-side member, the first fin protruding on the opposing surface side, the second fin being disposed on a lower pressure side in a rotating axis direction relative to the first fin and protruding on the opposing surface side. The thickness, in the rotating axis direction, of the second fin at the root thereof is greater than the thickness, in the rotating axis direction, of the first fin at the root thereof.
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公开(公告)号：US11852026B1
公开(公告)日：2023-12-26
申请号：US18095559
申请日：2023-01-11
发明人： Brian Nicholson
CPC分类号： F01D25/16 , F01D11/08 , F05D2240/307 , F05D2240/50
摘要： An exo-bearing system for a turbomachine is operable to improve aerodynamic efficiency and mechanical limits of rotor blades for fans, compressors, turbines, pumps and the like. The exo-bearing system is positioned between the tips of the blades and a surrounding structural housing. The exo-bearing system eliminates the air gap that is formed in prior art turbomachines and causes the blades to load in compression during operation which increases mechanical operability of the blades.
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公开(公告)号：US11852018B1
公开(公告)日：2023-12-26
申请号：US17818760
申请日：2022-08-10
发明人： Jacob John Kittleson
CPC分类号： F01D11/001 , F01D9/04 , F01D11/08 , F05D2220/32 , F05D2240/128 , F05D2240/55
摘要： A nozzle includes an endwall connected to an airfoil at one of a tip and root of the airfoil. The endwall includes a first and second side slash faces at respective circumferential edges thereof. The endwall also includes an inner surface extending between the first and second side slash faces. The inner surface includes a first planar surface portion adjacent to the first side slash face, a second planar surface portion adjacent to the second side slash face, and an arcuate surface portion extending between the first and second planar surface portions. The planar surface portions reduce a chute height by reducing hot gas path curvature locally along the side slash faces, which reduces working fluid ingestion between endwalls of the adjacent nozzles. The planar surface portions can be applied to an inner and/or an outer endwall of a nozzle.
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