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公开(公告)号：EP3587765A1
公开(公告)日：2020-01-01
申请号：EP19173793.1
申请日：2019-05-10
Applicant: United Technologies Corporation
Inventor： SUCIU, Gabriel L. , CHANDLER, Jesse M. , STAUBACH, Joseph Brent , MERRY, Brian D. , LORD, Wesley K.
Abstract: A gas turbine engine (20; 120) includes a main compressor section (20). A tap (110) is fluidly connected downstream of the main compressor section (24). A heat exchanger (112; 122; 130) is fluidly connected downstream of the tap (110). An auxiliary compressor unit (114; 140; 312) is fluidly connected downstream of the heat exchanger (112; 122; 130). The auxiliary compressor unit (114; 140; 312) is configured to compress air cooled by the heat exchanger (112; 122; 130) with an overall auxiliary compressor unit pressure ratio between 1.1 and 6.0. An intercooling system for a gas turbine engine is also disclosed.
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公开(公告)号：EP3569841A1
公开(公告)日：2019-11-20
申请号：EP19173765.9
申请日：2019-05-10
Applicant: United Technologies Corporation
Inventor： SUCIU, Gabriel L. , CHANDLER, Jesse M. , MERRY, Brian D. , SNAPE, Nathan
Abstract: A gas turbine engine (20) includes a plurality of rotating components housed within a compressor section (24) and a turbine section (28). A tap (110) connects to the compressor section (24). A heat exchanger (112; 164; 292; 312) connects downstream of the tap (110). A cooling compressor (114; 162) connects downstream of the heat exchanger (112; 164; 292; 312), and the cooling compressor (114; 162) connects to deliver air to at least one of the rotating components. A core housing (152) has an outer peripheral surface (153) and a fan housing (154) defines an inner peripheral surface (156). At least one bifurcation duct (158, 160; 406, 408) extends between the outer peripheral surface (153) to the inner peripheral surface (156). The heat exchanger (112; 164; 292; 312) is disposed within the at least one bifurcation duct (158, 160; 406, 408).
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公开(公告)号：EP3239497B1
公开(公告)日：2019-02-20
申请号：EP17167943.4
申请日：2017-04-25
Applicant: United Technologies Corporation
Inventor： STACK, Joseph , CHANDLER, Jesse M. , SUCIU, Gabriel , SOBANSKI, Kurt J.
IPC: F02C7/25
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公开(公告)号：EP3428426A1
公开(公告)日：2019-01-16
申请号：EP18193068.6
申请日：2016-04-13
Applicant: United Technologies Corporation
Inventor： SUCIU, Gabriel L. , CHANDLER, Jesse M. , HIPSKY, Harold W. , ZYWIAK, Thomas M.
Abstract: A nose cone assembly (64) for a gas turbine engine (20) and method (200) of circulating air in a gas turbine engine are disclosed. The nose cone assembly includes a nose cone (66) having an aperture (68) communicating air to an interior space (76) of the nose cone and a discharge member (74) communicating the air out of the nose cone.
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公开(公告)号：EP2902608B1
公开(公告)日：2018-12-26
申请号：EP15152453.5
申请日：2015-01-26
Applicant: United Technologies Corporation
Inventor： SUCIU, Gabriel L. , CHANDLER, Jesse M.
CPC classification number: F02K1/66 , F02C7/36 , F02K3/062 , F02K3/072 , F05D2260/4031
Abstract: A gas turbine engine (20) comprises an outer shroud (22). An inner core housing (24) is positioned radially inwardly of the outer shroud (22), and has a core engine including at least one compressor rotor (28) and at least one turbine rotor (32). A combustor section (40) is intermediate the at least one compressor rotor (28) and the at least one turbine rotor. A fan turbine is positioned downstream of the at least one turbine rotor (32). The fan turbine (44) drives a gear reduction (42) to, in turn, drive at least one fan blade (46,48) positioned radially inwardly of the outer shroud (22).
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Patent Agency Ranking
公开(公告)号：EP3121411B1
公开(公告)日：2018-12-12
申请号：EP16180657.5
申请日：2016-07-21
Applicant: United Technologies Corporation
Inventor： SNAPE, Nathan , SUCIU, Gabriel L. , MERRY, Brian D. , CHANDLER, Jesse M.
CPC classification number: F02C6/08 , F02C7/185 , F02C9/18 , F05D2220/3219 , F05D2260/211 , F05D2260/213 , Y02T50/671 , Y02T50/676
Abstract: A gas turbine engine comprises a main compressor section having a high pressure compressor with a downstream discharge, and more upstream locations. A turbine section has a high pressure turbine. A tap taps air from at least one of the more upstream locations in the compressor section, passing the tapped air through a heat exchanger and then to a cooling compressor. The cooling compressor compresses air downstream of the heat exchanger, and delivers air into the high pressure turbine. The heat exchanger also receives air to be delivered to an aircraft cabin. An intercooling system for a gas turbine engine is also disclosed.
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公开(公告)号：EP3406519A1
公开(公告)日：2018-11-28
申请号：EP18174158.8
申请日：2018-05-24
Applicant: United Technologies Corporation
Inventor： EPSTEIN, Alan H. , SUCIU, Gabriel L. , CHANDLER, Jesse M.
CPC classification number: B64C23/02 , B64C1/0009 , B64C5/08 , B64C21/00 , B64C21/06 , B64D2027/026 , B64D2033/0226
Abstract: A propulsion system for an aircraft (20) comprises at least two main gas turbine engines (26) and a plurality of dedicated boundary layer ingestion fans (28). An aircraft (20) is also disclosed.
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公开(公告)号：EP3049657B1
公开(公告)日：2018-10-03
申请号：EP14849046.9
申请日：2014-08-01
Applicant: United Technologies Corporation
Inventor： HILL, James D. , SUCIU, Gabriel L. , CHANDLER, Jesse M.
CPC classification number: F04D29/644 , B64D27/26 , B64D2027/264 , B64D2027/266 , F01D25/243 , F02C7/20 , F04D29/324 , F04D29/522 , F05D2220/32 , Y02T50/44 , Y02T50/671
Abstract: A mounting system for a gas turbine engine includes a compressor case portion, an inlet frame, an outlet frame, and a mounting structure. The compressor case portion houses rotatable compressor blades. The inlet frame connects to an inlet end of the compressor case. The outlet frame connects to an outlet end of the compressor case portion at an end opposite the compressor case inlet end. An axially fore mounting structure of the mounting structure connects to the inlet frame. An axially aft mounting structure of the mounting structure connects to the outlet frame. A bridging structure of the mounting structure is offset from the compressor case and connects the fore and aft mounting structures, thereby bridging engine loads across the inlet and outlet frames to reduce load induced distortion of the compressor case portion.
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公开(公告)号：EP2929163B1
公开(公告)日：2018-02-21
申请号：EP13862641.1
申请日：2013-06-20
Applicant: United Technologies Corporation
Inventor： SUCIU, Gabriel L. , CHANDLER, Jesse M.
CPC classification number: F02C7/18 , B64D2013/0603 , F01D25/12 , F02C6/08 , F02C9/18 , F02K3/06 , F02K3/062 , F05D2220/324 , F05D2220/327 , F05D2250/51 , Y02T50/675
Abstract: A gas turbine engine has a first source of air to be delivered into a core of the engine, and a second source of air, distinct from the first source of air and including separately controlled first and second fans, each delivering air into respective first and second conduits connected to distinct auxiliary applications.
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公开(公告)号：EP3273030A1
公开(公告)日：2018-01-24
申请号：EP17182673.8
申请日：2017-07-21
Applicant: United Technologies Corporation
Inventor： SUCIU, Gabriel L. , LORD, Wesley K. , CHANDLER, Jesse M. , ZYSMAN, Steven H.
CPC classification number: F02C7/18 , B64D27/20 , F02C3/04 , F05D2220/323 , F05D2250/51 , F05D2260/232 , Y02T50/676
Abstract: A gas turbine engine (21) has an inner housing surrounding a compressor (25), a combustor (27), and a turbine (29), with an inlet (23) leading into the compressor (25), and a cooling sleeve (28) defined radially outwardly of the inlet (23) to the compressor (25) for receiving cooling air radially outward of the compressor inlet (23). The cooling sleeve (28) extends along a length of the engine (21), and radially outwardly of the inner housing, with the cooling air in the cooling sleeve (28) being ejected at a downstream end to mix with products of combustion downstream of the turbine (29). An aircraft (17) is also disclosed.
Abstract translation: 燃气涡轮发动机（21）具有围绕压缩机（25），燃烧器（27）和涡轮机（29）的内壳体，其具有通向压缩机（25）的入口（23）和冷却套筒 （23）的径向外侧限定到压缩机（25），用于接收压缩机入口（23）的径向外部的冷却空气。 冷却套筒（28）沿着发动机（21）的长度并且在内部壳体的径向外部延伸，冷却套筒（28）中的冷却空气在下游端被喷射以与燃烧产物 涡轮机（29）。 还公开了一种飞机（17）。
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