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公开(公告)号：US20180187602A1
公开(公告)日：2018-07-05
申请号：US15907942
申请日：2018-02-28
Applicant: United Technologies Corporation
Inventor： Nathan Snape , Gabriel L. Suciu , Brian Merry , Jesse M. Chandler , Frederick M. Schwarz
CPC classification number: F02C7/143 , F02C6/08 , F02C7/185 , F02C7/32 , F02C9/18 , F02K3/06 , F05D2220/3218 , F05D2220/323 , F05D2260/211 , F05D2260/213 , Y02T50/672 , Y02T50/676
Abstract: A gas turbine engine includes a plurality of rotating components housed within a compressor section and a turbine section. A first tap is connected to the compressor section and configured to deliver air at a first pressure. A heat exchanger is connected downstream of the first tap and configured to deliver air to an aircraft fuselage. A cooling compressor is connected downstream of the heat exchanger. A high pressure feed is configured to deliver air at a second pressure which is higher than the first pressure. The cooling compressor is configured to deliver air to at least one of the plurality of rotating components. A valve assembly that can select whether air from the first tap or air from the high pressure feed is delivered to the aircraft pneumatic system.
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72.发明申请公开(公告)号：US20180156122A1
公开(公告)日：2018-06-07
申请号：US15369189
申请日：2016-12-05
Applicant: UNITED TECHNOLOGIES CORPORATION
Inventor： Frederick M. Schwarz , Nathan Snape
CPC classification number: F02C7/185 , F02C3/04 , F02C7/141 , F02C9/18 , F02K3/06 , F02K3/115 , F05D2260/213 , F05D2260/232 , F05D2270/01 , Y02T50/675
Abstract: A gas turbine engine has a fan rotor delivering air into a bypass duct defined between an outer fan case and an outer interior housing. The fan rotor also delivers air into a compressor section, a combustor, a turbine section. A chamber is defined between the outer interior housing and an inner housing. The inner housing contains the compressor section, the combustor and the turbine section. A first conduit taps hot compressed air to be cooled and passes the air to at least one heat exchanger. The air is cooled in the heat exchanger and returned to a return conduit. The return conduit passes the cooled air to at least one of the turbine section and the compressor section. The heat exchanger has a core exhaust plane. The turbine section has at least a first and a downstream second rotor blade row, with the core exhaust plane located downstream of a center plane of the second blade row.
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公开(公告)号：US20180128179A1
公开(公告)日：2018-05-10
申请号：US15346169
申请日：2016-11-08
Applicant: United Technologies Corporation
Inventor： Joseph B. Staubach , Nathan Snape
CPC classification number: F02C7/185 , F02C3/04 , F02C9/18 , F02K3/077 , F05D2220/32 , F05D2260/212 , F05D2260/213 , Y02T50/675
Abstract: An intercooled cooling system for a gas turbine engine is provided. The intercooled cooling system includes a plurality of cooling stages in fluid communication with an air stream utilized for cooling. A first cooling stage of the plurality of cooling stages is fluidly coupled to a bleed port of a compressor of the gas turbine engine to receive and cool bleed air with the air stream to produce a cool bleed air. The intercooled cooling system also includes a pump fluidly coupled to the first cooling stage to receive the cool bleed air and increase a pressure of the cool bleed air to produce a pressurized cool bleed air. A second cooling stage of the plurality of cooling stages is fluidly coupled to the pump to receive and cool the pressurized cool bleed air to produce an intercooled cooling air, which is provided to the gas turbine engine.
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公开(公告)号：US20180128176A1
公开(公告)日：2018-05-10
申请号：US15346206
申请日：2016-11-08
Applicant: UNITED TECHNOLOGIES CORPORATION
Inventor： Joseph B. Staubach , Nathan Snape
Abstract: An intercooled cooling system for a gas turbine engine is provided. The intercooled cooling system includes cooling stages in fluid communication with an air stream utilized for cooling. A first cooling stage is fluidly coupled to a bleed port of the gas turbine engine to receive and cool bleed air with the air stream to produce a cool bleed air. The intercooled cooling system includes a pump fluidly coupled to the first cooling stage to receive and increase a pressure of the cool bleed air to produce a pressurized cool bleed air. A second cooling stage is fluidly coupled to the pump to receive and cool the pressurized cool bleed air to produce an intercooled cooling air. The intercooled cooling system includes an air cycle machine in fluid communication to outputs of the cooling stages to selectively receive the cool bleed air or the intercooled cooling air.
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公开(公告)号：US20180080389A1
公开(公告)日：2018-03-22
申请号：US15271274
申请日：2016-09-21
Applicant: UNITED TECHNOLOGIES CORPORATION
Inventor： Frederick M. Schwarz , Nathan Snape
CPC classification number: F02C9/18 , F02C7/185 , F02K3/115 , F05D2260/213 , F05D2260/80 , F05D2270/053 , F05D2270/112 , F05D2270/301 , G01M15/09 , Y02T50/675
Abstract: A gas turbine engine has a compressor section and a turbine section. A secondary cooling air includes a first fluid connection to tap cooling air and pass the cooling air through a plurality of tubes, and a second fluid connection for returning air from the tubes back to at least one of the compressor and turbine for cooling. A sensor senses a condition of the cooling air downstream of the tubes and a control compares the sensed condition of the cooling air to an expected condition, and to identify a potential concern in the cooling air system should the sensed condition differ from the expected condition by more than a predetermined amount.
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Patent Agency Ranking
公开(公告)号：US20180058332A1
公开(公告)日：2018-03-01
申请号：US15803418
申请日：2017-11-03
Applicant: United Technologies Corporation
Inventor： Hung Duong , Nathan Snape , Gabriel L. Suciu
IPC: F02C7/32 , F02C3/04 , F02C7/36 , F16H57/038 , F16H57/025 , F01D15/12 , F16H1/22 , F16H57/02
CPC classification number: F02C7/32 , F01D15/12 , F02C3/04 , F02C7/36 , F05D2250/11 , F05D2250/314 , F05D2260/4031 , F05D2260/532 , F16H1/222 , F16H57/02 , F16H57/025 , F16H57/038
Abstract: A gas turbine engine assembly comprising, a gearbox including a first housing that includes a first auxiliary gear drive on a first portion thereof, a second housing that includes a second auxiliary gear drive on a second portion thereof, and a third housing that includes a third auxiliary gear drive on a third portion thereof, the housings being interconnected so that the first portion of the first housing, the second portion of the second housing and the third portion of the third housing form a substantially triangular polyhedron shape, with the second portion of the second housing disposed between the first portion of the first housing and the third portion of the third housing. The first auxiliary gear drive, the second auxiliary gear drive and the third auxiliary gear drive project outwardly in mutually divergent directions.
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公开(公告)号：US09714610B2
公开(公告)日：2017-07-25
申请号：US13645067
申请日：2012-10-04
Applicant: United Technologies Corporation
Inventor： Nathan Snape , Gabriel L. Suciu , Simon Pickford , Allan R. Penda
CPC classification number: F02C6/08 , F02C7/14 , F05D2260/213 , Y02T50/672 , Y02T50/675
Abstract: An air-oil cooler (AOC) for a gas turbine engine is disclosed. The AOC may comprise an oil inlet, an oil outlet, and heat exchange elements between the oil inlet and the oil outlet. The AOC may be longitudinally positioned between a fan and a V-groove of the engine and radially spaced between a low pressure compressor and a low pressure compressor panel. A gas turbine engine comprising an AOC is disclosed. The AOC of the engine may comprise an oil inlet, an oil outlet, and heat exchange elements between the oil inlet and the oil outlet. The AOC of the engine may be longitudinally positioned between a fan and a V-groove of the engine and radially spaced between a low pressure compressor and a low pressure compressor panel. A method of operating an AOC for use on a gas turbine engine is also disclosed.
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公开(公告)号：US20170082028A1
公开(公告)日：2017-03-23
申请号：US15069197
申请日：2016-03-14
Applicant: United Technologies Corporation
Inventor： Hung Duong , Gabriel L. Suciu , Nathan Snape
CPC classification number: F02C7/185 , F02C3/04 , F02C7/18 , F02C7/32 , F02K3/115 , F05D2260/211 , F05D2260/213 , F05D2260/4031 , F05D2260/606 , Y02T50/676
Abstract: A gas turbine engine includes a main compressor section having a high pressure compressor with a downstream discharge, and 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 main compressor section. The tap passes the tapped air through a heat exchanger and then to a cooling compressor compressing air downstream of the heat exchanger. The cooling compressor delivers compressed air into the turbine section. An accessory gear box drives the cooling compressor. An intercooling system for a gas turbine engine is also disclosed.
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公开(公告)号：US20160280387A1
公开(公告)日：2016-09-29
申请号：US14667975
申请日：2015-03-25
Applicant: United Technologies Corporation
Inventor： Nathan Snape , James D. Hill , Gabriel L. Suciu , Brian D. Merry
IPC: B64D33/02
CPC classification number: F02C7/14 , F05D2260/213 , F05D2260/232 , F05D2260/98 , Y02T50/671 , Y02T50/675
Abstract: An aircraft thermal management system includes a first fluid system containing a first fluid, a fluid loop containing a thermally neutral heat transfer fluid, a second fluid system containing a second fluid, a first heat exchanger configured to transfer heat from the first fluid to the thermally neutral heat transfer fluid, and a second heat exchanger configured to transfer heat from the thermally neutral heat transfer fluid to the second fluid. The fluid loop is configured to provide the thermally neutral heat transfer fluid to the first heat exchanger at a pressure that matches the pressure of the first fluid.
Abstract translation: 飞机热管理系统包括第一流体系统，其包含第一流体，包含热中性传热流体的流体回路，包含第二流体的第二流体系统，被配置为将热量从第一流体传递到热 中性传热流体和被配置为将热量从热中性传热流体传递到第二流体的第二热交换器。 流体回路构造成以与第一流体的压力匹配的压力将热中性传热流体提供给第一热交换器。
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公开(公告)号：US20160177830A1
公开(公告)日：2016-06-23
申请号：US14910283
申请日：2014-08-01
Applicant: UNITED TECHNOLOGIES CORPORATION
Inventor： Vito Guardi , Christopher B. Lyons , Nathan Snape
CPC classification number: F02C7/18 , F01D5/18 , F01D9/065 , F01D25/14 , F02C3/04 , F02C6/08 , F02C7/185 , F02C9/18 , F05D2220/32 , F05D2240/35 , F05D2260/20 , F23R3/283 , F23R3/286 , Y02T50/676
Abstract: A turbine engine includes a compressor section, a combustor in fluid communication with the compressor section, and a turbine section in fluid communication with the combustor. Also included in the turbine engine is a mixing chamber. The mixing chamber is located between the compressor section and the combustor section and the mixing chamber is radially outward of a primary fluid flow path connecting the compressor section, the combustor section, and the turbine section.
Abstract translation: 涡轮发动机包括压缩机部分，与压缩机部分流体连通的燃烧器和与燃烧器流体连通的涡轮部分。 涡轮发动机中还包括混合室。 混合室位于压缩机部分和燃烧器部分之间，并且混合室在连接压缩机部分，燃烧器部分和涡轮部分的主流体流动路径的径向外侧。
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