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公开(公告)号：US09121367B2
公开(公告)日：2015-09-01
申请号：US13869057
申请日：2013-04-24
Applicant: UNITED TECHNOLOGIES CORPORATION
Inventor： Hasel Karl , Joseph B. Staubach , Brian D. Merry , Gabriel L. Suciu , Christopher M. Dye
CPC classification number: F02K3/025 , F02C3/107 , F02C7/00 , F02K3/06 , F05D2260/4031
Abstract: A gas turbine engine has a fan section, a gear arrangement configured to drive the fan section, a compressor section, including both a low pressure compressor section and a high pressure compressor section. A turbine section is configured to drive the compressor section and the gear arrangement. An overall pressure ratio provided by the combination of a pressure ratio across the low pressure compressor section and a pressure ratio across the high pressure compressor section is greater than about 35. The pressure ratio across a first of the low and high pressure compressor sections is between about 3 and about 8. The pressure ratio across a second of the low and high pressure compressor sections is between about 7 and about 15. The fan is configured to deliver a portion of air into the compressor section, and a portion of air into a bypass duct.
Abstract translation: 燃气涡轮发动机具有风扇部，构造成驱动风扇部的齿轮装置，包括低压压缩部和高压压缩部两者的压缩部。 涡轮部分构造成驱动压缩机部分和齿轮装置。 通过低压压缩机部分的压力比和高压压缩机部分的压力比的组合提供的总压力比大于约35。第一低压压缩机部分和高压压缩机部分之间的压力比在 约3和约8之间。跨过第二个低压和高压压缩机段的压力比在约7至约15之间。风扇构造成将一部分空气输送到压缩机部分中，并且一部分空气进入 旁路管道。
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公开(公告)号：US20150226117A1
公开(公告)日：2015-08-13
申请号：US14597510
申请日：2015-01-15
Applicant: United Technologies Corporation
Inventor： Gabriel L. Suciu , Michael E. McCune , Jesse M. Chandler , Alan H. Epstein , Steven M. O'Flarity , Christopher J. Hanlon , William F. Schneider , Joseph B. Staubach , James A. Kenyon
CPC classification number: F02C3/107 , B64D27/18 , B64D35/04 , F01D13/003 , F02C3/06 , F02C3/067 , F02C7/36 , F02C9/18 , F02K3/077 , F05D2220/323 , F05D2220/36 , F05D2240/40 , F05D2250/312
Abstract: A gas generator has at least one compressor rotor, at least one gas generator turbine rotor and a combustion section. A fan drive turbine is positioned downstream of a path of the products of combustion having passed over the at least one gas generator turbine rotor. The fan drive turbine drives a shaft and the shaft engages gears to drive at least three fan rotors.
Abstract translation: 气体发生器具有至少一个压缩机转子，至少一个气体发生器涡轮机转子和燃烧部分。 风扇驱动涡轮机位于已经通过至少一个气体发生器涡轮机转子的燃烧产物的路径的下游。 风扇驱动涡轮机驱动轴并且轴接合齿轮以驱动至少三个风扇转子。
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公开(公告)号：US20140174055A1
公开(公告)日：2014-06-26
申请号：US14102764
申请日：2013-12-11
Applicant: United Technologies Corporation
Inventor： Paul R. Adams , Shankar S. Magge , Joseph B. Staubach , Wesley K. Lord , Frederick M. Schwarz
CPC classification number: F02C9/18 , F01D1/02 , F01D5/02 , F01D9/041 , F01D25/24 , F02C3/04 , F02C3/107 , F02C3/113 , F02C7/20 , F02C7/36 , F02K3/025 , F02K3/06 , F02K3/075 , F02K7/06 , F05D2220/32 , F05D2260/40311 , F05D2260/606 , Y02T50/671
Abstract: A turbofan engine is disclosed and includes a fan and a compressor in communication with the fan section, a combustor, a turbine and a speed reduction mechanism coupled to the fan and rotatable by the turbine. The turbine includes a first turbine section that includes three or more stages and a second turbine section that includes at least two stages. A ratio of airfoils in the first turbine section to a bypass area is less than about 170.
Abstract translation: 涡轮风扇发动机被公开并且包括与风扇部分连通的风扇和压缩机，燃烧器，涡轮机和联接到风扇并由涡轮机旋转的减速机构。 涡轮机包括包括三级或更多级的第一涡轮机部分和包括至少两级的第二涡轮部分。 第一涡轮部分中的翼型件与旁路区域的比例小于约170。
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公开(公告)号：US20140157755A1
公开(公告)日：2014-06-12
申请号：US14179743
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 gas turbine engine has a fan section, including a fan, a gear arrangement configured to drive the fan section, and a compressor section, including both a first compressor and a second compressor. A turbine section is configured to drive the compressor section and the gear arrangement. An overall pressure ratio is provided by the combination of the first compressor and the second compressor. The fan is configured to deliver a portion of air into the compressor section, and a portion of air into a bypass duct. A bypass ratio which is defined as a volume of air passing to the bypass duct compared to a volume of air passing into the compressor section is greater than or equal to about 8.
Abstract translation: 一种燃气涡轮发动机具有风扇部分，包括风扇，构造成驱动风扇部分的齿轮装置和包括第一压缩机和第二压缩机的压缩机部分。 涡轮部分构造成驱动压缩机部分和齿轮装置。 总压力比由第一压缩机和第二压缩机的组合提供。 风扇被配置为将一部分空气输送到压缩机部分中，并且一部分空气进入旁通管道。 被定义为与通过压缩机部分的空气体积相比通过旁通管道的空气体积的旁路比大于或等于约8。
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公开(公告)号：US20130202415A1
公开(公告)日：2013-08-08
申请号：US13836799
申请日：2013-03-15
Applicant: United Technologies Corporation
Inventor： Hasel Karl , Joseph B. Staubach , Brian D. Merry , Gabriel L. Suciu , Christopher M. Dye
IPC: F02K3/02
CPC classification number: F02K3/025 , F02C3/107 , F02C7/00 , F02K3/06 , F05D2260/4031
Abstract: A gas turbine engine includes a fan section, a gear arrangement configured to drive the fan section, a compressor section and a turbine section. The compressor section includes a low pressure compressor section and a high pressure compressor section. The turbine section is configured to drive compressor section and the gear arrangement. The engine includes a combination of quantities providing beneficial operation.
Abstract translation: 燃气涡轮发动机包括风扇部分，被配置为驱动风扇部分的齿轮装置，压缩机部分和涡轮部分。 压缩机部分包括低压压缩机部分和高压压缩机部分。 涡轮部分构造成驱动压缩机部分和齿轮装置。 发动机包括提供有益操作的量的组合。
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Patent Agency Ranking
公开(公告)号：US11519289B2
公开(公告)日：2022-12-06
申请号：US16706058
申请日：2019-12-06
Applicant: UNITED TECHNOLOGIES CORPORATION
Inventor： Gabriel L. Suciu , Om P. Sharma , Joseph B. Staubach , Marc J. Muldoon , Jesse M. Chandler , David Lei Ma
Abstract: A hybrid electric gas turbine engine includes a fan section having a fan, a turbine section having a turbine drivably connected to the fan through a main shaft that extends along a central longitudinal axis, a gas generating core extending along a first axis that is radially offset from the central longitudinal axis, and an electric motor drivably connected to the main shaft, wherein the electric motor is colinear with the main shaft.
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公开(公告)号：US11255263B2
公开(公告)日：2022-02-22
申请号：US16733504
申请日：2020-01-03
Applicant: United Technologies Corporation
Inventor： Marc J. Muldoon , Joseph B. Staubach , Jesse M. Chandler , Neil Terwilliger , Gabriel L. Suciu
Abstract: An aircraft propulsion system includes a fan section that includes a fan shaft that is rotatable about a fan axis. The fan shaft includes a fan gear. The aircraft propulsion system also includes a boost turbine engine that includes a first output shaft that includes a first gear that is coupled to the fan gear. The boost turbine engine has a first maximum power capacity. The aircraft propulsion system further includes a cruise gas turbine engine that includes a second output shaft that includes a second gear that is coupled to the fan gear. The cruise turbine engine has a second maximum power capacity that is less than the first maximum power capacity of the boost turbine engine. The fan section produces a thrust that corresponds to power input through the fan gear from the boost turbine engine and the cruise turbine engine.
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公开(公告)号：US20210301729A1
公开(公告)日：2021-09-30
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：US20210301720A1
公开(公告)日：2021-09-30
申请号：US16832535
申请日：2020-03-27
Applicant: United Technologies Corporation
Inventor： Joseph B. Staubach , Amanda J. L. Boucher
IPC: F02C7/141
Abstract: Gas turbine engines are described. The gas turbine engines include a compressor section, a combustor section, a turbine section, and a nozzle, wherein the compressor section, the combustor section, the turbine section, and the nozzle define a core flow path that expels through the nozzle. A waste heat recovery system is operably connected to the gas turbine engine, the waste heat recovery system having a working fluid. An auxiliary cooling system is configured to provide cooling to a working fluid of the waste heat recovery system.
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公开(公告)号：US11073085B2
公开(公告)日：2021-07-27
申请号：US15346169
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 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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