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公开(公告)号：US10794293B2
公开(公告)日：2020-10-06
申请号：US16025094
申请日：2018-07-02
Applicant: United Technologies Corporation
Inventor： Paul R. Adams , Shankar S. Magge , Joseph B. Staubach , Wesley K. Lord , Frederick M. Schwarz , Gabriel L. Suciu
IPC: F02C7/36 , F02C3/107 , F02C9/18 , F02K3/06 , F02K3/075 , F01D5/06 , F01D25/24 , F02C3/04 , F02C7/20 , F04D19/02 , F01D11/12
Abstract: A turbofan engine according to an example of the present disclosure includes, among other things, an engine case and a gaspath through the engine case. A fan has a circumferential array of fan blades. The engine further has a compressor, a combustor, a gas generating turbine, and a low pressure turbine section. A speed reduction mechanism couples the low pressure turbine section to the fan. A bypass area ratio is greater than about 6.0. The low pressure turbine section airfoil count to bypass area ratio is below about 170.
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公开(公告)号：US10794273B2
公开(公告)日：2020-10-06
申请号：US14789036
申请日：2015-07-01
Applicant: UNITED TECHNOLOGIES CORPORATION
Inventor： Jeffery F. Perlak , Joseph B. Staubach , Gabriel L. Suciu , James D. Hill , Frederick M. Schwarz
Abstract: A gas turbine engine according to the present disclosure includes a first compressor and a first turbine for driving the first compressor. A core section includes a second compressor and a second turbine for driving the second compressor. A third turbine is arranged fluidly downstream of the first turbine and the second turbine and configured to drive a power take-off. A first duct system is arranged fluidly between the low-pressure compressor and the core section. The first duct system is arranged to reverse fluid flow before entry into the core section.
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23.发明申请公开(公告)号：US20200224588A1
公开(公告)日：2020-07-16
申请号：US16248861
申请日：2019-01-16
Applicant: United Technologies Corporation
Inventor： Nagendra Somanath , Brendan T. McAuliffe , Joseph B. Staubach
Abstract: A gas turbine engine includes a primary flowpath fluidly connecting a compressor section, a combustor section, and a turbine section. A heat exchanger is disposed in the primary flowpath downstream of the turbine section. The heat exchanger includes a first inlet for receiving fluid from the primary flowpath and a first outlet for expelling fluid received at the first inlet. The heat exchanger further includes a second inlet fluidly connected to a supercritical CO2 (sCO2) bottoming cycle and a second outlet connected to the sCO2 coolant circuit. The sCO2 bottoming cycle is a recuperated Brayton cycle.
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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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Patent Agency Ranking
公开(公告)号：US20170002735A1
公开(公告)日：2017-01-05
申请号：US14789036
申请日：2015-07-01
Applicant: UNITED TECHNOLOGIES CORPORATION
Inventor： Jeffery F. Perlak , Joseph B. Staubach , Gabriel L. Suciu , James D. Hill , Frederick M. Schwarz
IPC: F02C3/107
CPC classification number: F02C3/107 , F02C3/10 , F02C3/145 , F05D2210/44 , F05D2260/4031
Abstract: A gas turbine engine according to the present disclosure includes a first compressor and a first turbine for driving the first compressor. A core section includes a second compressor and a second turbine for driving the second compressor. A third turbine is arranged fluidly downstream of the first turbine and the second turbine and configured to drive a power take-off. A first duct system is arranged fluidly between the low-pressure compressor and the core section. The first duct system is arranged to reverse fluid flow before entry into the core section.
Abstract translation: 根据本公开的燃气涡轮发动机包括第一压缩机和用于驱动第一压缩机的第一涡轮机。 核心部分包括用于驱动第二压缩机的第二压缩机和第二涡轮机。 第三涡轮机布置在第一涡轮机和第二涡轮机的流体下游并被配置成驱动动力输出。 第一管道系统流体地布置在低压压缩机和铁芯段之间。 第一管道系统布置成在进入核心部分之前逆转流体流动。
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公开(公告)号：US20140260183A1
公开(公告)日：2014-09-18
申请号：US14142966
申请日：2013-12-30
Applicant: UNITED TECHNOLOGIES CORPORATION
Inventor： Gabriel L. Suciu , Jesse M. Chandler , Joseph B. Staubach
CPC classification number: F02C7/057 , B64D27/20 , B64D33/02 , B64D2033/0286 , F02C3/10 , F02C7/042 , F02C7/052 , F02C7/055 , F02K3/077 , F05D2250/314
Abstract: A gas generator for a reverse core engine propulsion system has a variable cycle intake for the gas generator, which variable cycle intake includes a duct system. The duct system is configured for being selectively disposed in a first position and a second position, wherein free stream air is fed to the gas generator when in the first position, and fan stream air is fed to the gas generator when in the second position.
Abstract translation: 用于逆向核心发动机推进系统的气体发生器具有用于气体发生器的可变循环进气口，该可变循环进气口包括管道系统。 管道系统被配置为选择性地设置在第一位置和第二位置，其中当处于第一位置时，自由流空气被供给到气体发生器，并且当处于第二位置时，风扇流空气被供给到气体发生器。
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公开(公告)号：US20140157752A1
公开(公告)日：2014-06-12
申请号：US14179827
申请日：2014-02-13
Applicant: UNITED TECHNOLOGIES CORPORATION
Inventor： Karl L. Hasel , Joseph B. Staubach , Brian D. Merry , Gabriel L. Suciu , Christopher M. Dye
IPC: F02K3/06
CPC classification number: F02K3/06 , F02C3/107 , F05D2260/4031
Abstract: A method of designing a gas turbine engine includes providing a fan section including a fan; driving the fan section via a gear arrangement; providing a compressor section, including both a first compressor and a second compressor; and driving the compressor section and the gear arrangement via a turbine section. The pressure ratio across the first compressor is greater than or equal to about 7.
Abstract translation: 一种设计燃气涡轮发动机的方法包括：提供包括风扇的风扇部分; 通过齿轮装置驱动风扇部分; 提供包括第一压缩机和第二压缩机的压缩机部分; 并且经由涡轮机部分驱动压缩机部分和齿轮装置。 跨越第一压缩机的压力比大于或等于约7。
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公开(公告)号：US11629647B2
公开(公告)日：2023-04-18
申请号：US16832614
申请日：2020-03-27
Applicant: United Technologies Corporation
Inventor： Joseph B. Staubach , Amanda J. L. Boucher
Abstract: Waste heat management systems are described. The waste heat management systems include a turbine engine having a compressor section, a combustor section, a turbine section, and a nozzle. The compressor section, the combustor section, the turbine section, and the nozzle define a core flow path that expels through the nozzle. The waste heat management systems also include an auxiliary power unit (APU) system and a waste heat recovery system operably connected to the APU system. The APU system is integrated into a working fluid flow path of the waste heat recovery system.
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公开(公告)号：US11230948B2
公开(公告)日：2022-01-25
申请号：US16248884
申请日：2019-01-16
Applicant: United Technologies Corporation
Inventor： Brendan T. McAuliffe , Joseph B. Staubach , Nagendra Somanath
Abstract: A gas turbine engine includes a primary flowpath fluidly connecting a compressor section, a combustor section, and a turbine section. A heat exchanger is disposed in the primary flowpath downstream of the turbine section. The heat exchanger includes a first inlet for receiving fluid from the primary flowpath and a first outlet for expelling fluid received at the first inlet. The heat exchanger further includes a second inlet fluidly connected to a supercharged CO2 (sCO2) bottoming cycle and a second outlet connected to the sCO2 bottoming cycle. The sCO2 bottoming cycle is an overexpanded, recuperated Brayton cycle.
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