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公开(公告)号：US20180045138A1
公开(公告)日：2018-02-15
申请号：US14617366
申请日：2015-02-09
Applicant: United Technologies Corporation
Inventor： Gabriel L. Suciu , Nathan Snape , Anthony R. Bifulco , William K. Ackermann , Becky E. Rose , Jesse M. Chandler
CPC classification number: F02K1/04 , F01D15/08 , F01D25/12 , F01D25/125 , F01D25/14 , F02C7/04 , F02C7/047 , F02C7/057 , F02C7/14 , F02C7/18 , F02C7/185 , F02C7/32 , F05D2220/32 , F05D2260/20 , F05D2260/213
Abstract: A nose cone assembly for a gas turbine engine and method of circulating air in a gas turbine engine are disclosed. The nose cone assembly includes a nose cone having an aperture communicating air to an interior space of the nose cone and a discharge member communicating the air out of the nose cone.
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公开(公告)号：US20170254268A1
公开(公告)日：2017-09-07
申请号：US15058229
申请日：2016-03-02
Applicant: UNITED TECHNOLOGIES CORPORATION
Inventor： Wesley K. Lord , Nathan Snape , Gabriel L. Suciu
IPC: F02C7/18
Abstract: A gas turbine engine component includes a heat exchange structure having an upstream end and a downstream end. A diffusing duct is associated with the upstream end. A throttle member controls air flow through the heat exchange structure, wherein the throttle member: (a) has a non-circular cross section; and (b) is mounted to the downstream end of the heat exchange structure or is mounted between the upstream end and the diffusing duct.
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公开(公告)号：US20160237906A1
公开(公告)日：2016-08-18
申请号：US14745539
申请日：2015-06-22
Applicant: United Technologies Corporation
Inventor： Gabriel L. Suciu , Jesse M. Chandler , Brian D. Merry , Nathan Snape
CPC classification number: F02C7/18 , F05D2260/213 , 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, passes 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. A core housing has an outer peripheral surface and a fan housing defining an inner peripheral surface. At least one bifurcation duct extends between the outer peripheral surface to the inner peripheral surface. The heat exchanger is received within the at least one bifurcation duct.
Abstract translation: 燃气涡轮发动机包括具有下游排出口的高压压缩机的主压缩机部分和更多的上游位置。 涡轮机部分具有高压涡轮机。 抽头从压缩机部分中的上游位置中的至少一个抽头抽吸空气，将抽头的空气通过热交换器，然后传递到冷却压缩机。 冷却压缩机压缩热交换器下游的空气，并将空气输送到高压涡轮机中。 芯壳体具有外周表面和限定内周表面的风扇壳体。 至少一个分叉管在外周表面和内周表面之间延伸。 热交换器被容纳在至少一个分叉管内。
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公开(公告)号：US20160230843A1
公开(公告)日：2016-08-11
申请号：US14617428
申请日：2015-02-09
Applicant: United Technologies Corporation
Inventor： Hung Duong , Nathan Snape
IPC: F16H1/22 , F16H1/20 , F16H57/021 , F02C7/32
CPC classification number: F16H1/22 , F02C7/32 , F02K3/06 , F05D2250/312 , F05D2260/53 , F16H1/206 , F16H57/021
Abstract: A gearbox for a gas turbine engine includes a housing that includes a cavity provided between opposing first and second mounting surfaces. An input gear shaft is coupled to a drive gear. The drive gear is connected to first and second shaft portions that respectively extend to the first and second mounting surfaces. The first and second shaft portions and the drive gear are coaxial with one another.
Abstract translation: 用于燃气涡轮发动机的齿轮箱包括壳体，该壳体包括设置在相对的第一和第二安装表面之间的空腔。 输入齿轮轴联接到驱动齿轮。 驱动齿轮连接到分别延伸到第一和第二安装表面的第一和第二轴部分。 第一和第二轴部分和驱动齿轮彼此同轴。
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公开(公告)号：US20160208698A1
公开(公告)日：2016-07-21
申请号：US14600445
申请日：2015-01-20
Applicant: United Technologies Corporation
Inventor： Nathan Snape , Gabriel L. Suciu , Brian D. Merry , James D. Hill , William Ackermann
IPC: F02C7/12
CPC classification number: F02C7/12 , F05D2260/213
Abstract: The present disclosure provides systems and methods related to thermal management systems for gas turbine engines. For example, a thermal management system comprises a thermally neutral heat transfer fluid circuit, a first heat exchanger disposed on the fluid circuit, and a second heat exchanger disposed on the fluid circuit.
Abstract translation: 本公开提供了与燃气涡轮发动机的热管理系统相关的系统和方法。 例如，热管理系统包括热中性传热流体回路，设置在流体回路上的第一热交换器和设置在流体回路上的第二热交换器。
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Patent Agency Ranking
公开(公告)号：US20150267617A1
公开(公告)日：2015-09-24
申请号：US14729800
申请日：2015-06-03
Applicant: United Technologies Corporation
Inventor： Gabriel L. Suciu , Allan R. Penda , Brian D. Merry , Christopher M. Dye , Nathan Snape
CPC classification number: F02C7/185 , F02C7/08 , F02C7/14 , F02C7/18 , Y02T50/671
Abstract: A thermal system for a gas turbine engine includes a bypass flow duct and a compressor flow duct which meets with the bypass flow duct at an intersection. A valve is located within the intersection and is movable between a first position and a second position. First position is operable to selectively communicate fan bypass flow from the bypass flow duct and block the compressor flow duct. The second position is operable to selectively block the bypass flow duct and communicate bleed flow through the compressor flow duct.
Abstract translation: 用于燃气涡轮发动机的热系统包括在交叉口处与旁路流动管道相交的旁通流动管道和压缩机流动管道。 阀位于交叉口内，并可在第一位置和第二位置之间移动。 第一位置可操作以选择性地使来自旁路流动管道的风扇旁路流动并且阻塞压缩机流动管道。 第二位置可操作以选择性地阻挡旁路流动管道并且连通通过压缩机流动管道的排出流。
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公开(公告)号：US20140165588A1
公开(公告)日：2014-06-19
申请号：US13715202
申请日：2012-12-14
Applicant: UNITED TECHNOLOGIES CORPORATION
Inventor： Nathan Snape , Brian D. Merry , Allan R. Penda , Gabriel L. Suciu
IPC: F02C9/18
Abstract: A disclosed bleed air system utilizes high pressure air from a high pressure compressor to drive the turbo compressor to increase a pressure of bleed air drawn from the low pressure compressor. Air drawn from the low pressure compressor is at a lower temperature and pressure than that encountered from the high pressure compressor. The turbo compressor increases the pressure of airflow and provides that airflow into the main bleed air passage to be communicated to systems utilizing the bleed air.
Abstract translation: 公开的泄放空气系统利用来自高压压缩机的高压空气来驱动涡轮压缩机以增加从低压压缩机抽出的排出空气的压力。 从低压压缩机抽出的空气的压力低于高压压缩机所遇到的温度和压力。 涡轮压缩机增加了气流的压力，并且使得流入主排气通道的气流被传送到利用排放空气的系统。
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公开(公告)号：US11428121B2
公开(公告)日：2022-08-30
申请号：US16375892
申请日：2019-04-05
Applicant: United Technologies Corporation
Inventor： Frederick M. Schwarz , Nathan Snape
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. A flowpath is defined between a rotating surface and a non-rotating surface. The flowpath is connected downstream of the heat exchanger and is configured to deliver air to at least one of the plurality of rotating components. At least a portion of the non-rotating surface and the rotating surface includes a base metal. An insulation material is disposed on a surface along the flowpath.
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公开(公告)号：US11346288B2
公开(公告)日：2022-05-31
申请号：US15271274
申请日：2016-09-21
Applicant: UNITED TECHNOLOGIES CORPORATION
Inventor： Frederick M. Schwarz , Nathan Snape
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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公开(公告)号：US11236675B2
公开(公告)日：2022-02-01
申请号：US16821383
申请日：2020-03-17
Applicant: United Technologies Corporation
Inventor： Nathan Snape
Abstract: A gas turbine engine has a compressor section with a downstream most end and a cooling air tap at a location spaced upstream from the downstream most end. The cooling air tap is passed through at least one boost compressor and at least one heat exchanger, and then passed to a turbine section to cool the turbine section. The boost compressor is driven by a driveshaft which is driven by the turbine section. A boost turbine selectively drives the boost compressor.
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