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1. 发明授权

US11230975B2 Modulated fire extinguishing vent for a gas turbine engine 有权
公开(公告)号：US11230975B2
公开(公告)日：2022-01-25
申请号：US16358760
申请日：2019-03-20
申请人： United Technologies Corporation
发明人： Nigel David Sawyers-Abbott , Federico Papa
IPC分类号： F02C7/25 , A62C3/08 , F02C9/18 , F02C9/34 , F02K3/04 , B64D45/00
摘要： A gas turbine engine includes an engine core having a compressor, a combustor fluidly connected to the compressor, and a turbine fluidly connected to the combustor. A core nacelle is disposed radially outward of the engine core. A cavity is disposed between an inner surface of the core nacelle and an outer surface of the engine core. The cavity includes a vent disposed at an aft end. The vent includes at least one flap configured to be maintained in an unrestricted position and in a restricted position. An actuator is configured to control the position of the at least one flap.

2. 发明授权

US10294873B2 Aircraft bleed system 有权
公开(公告)号：US10294873B2
公开(公告)日：2019-05-21
申请号：US15420808
申请日：2017-01-31
申请人： United Technologies Corporation
发明人： Federico Papa , Bradley C Farnum , Kristin Kopp-Vaughan , Nathan Roe
IPC分类号： F02C9/18 , B64D13/02 , B64D13/08 , F02C6/08 , B64D13/00 , B64D15/04 , F02C7/047 , F02C7/18 , B64D13/06 , B64D33/02
摘要： A method of controlling an aircraft bleed may include the steps of monitoring a temperature of a precooled airflow exiting a precooler, and determining a status of a wing anti-ice system of an aircraft. The wing anti-ice system may be configured to receive the precooled airflow from the precooler. The method may further comprise the steps of determining whether an engine operating condition of the aircraft is within an icing envelope, selecting a temperature set point for the precooled airflow based on the status of the wing anti-ice system and whether the aircraft is within an icing envelope, and modulating a fan airflow from a fan to the precooler to adjust the temperature of the precooled airflow to the temperature set point.

3. 发明申请

US20140360153A1 GAS TURBINE ENGINE THERMAL MANAGEMENT SYSTEM 审中-公开
标题翻译：气体涡轮发动机热管理系统
公开(公告)号：US20140360153A1
公开(公告)日：2014-12-11
申请号：US14247575
申请日：2014-04-08
申请人： United Technologies Corporation
发明人： Federico Papa , Thomas G. Phillips , Kathleen R. Phillips , Ethan K. Stearns , Justin W. Heiss
IPC分类号： F02C7/12 , F02C7/224 , G05D7/06 , F02C9/48 , F02C7/06 , G05B15/02 , F02C3/08 , F02C7/232
CPC分类号： F02C7/12 , F01D25/12 , F02C3/08 , F02C7/06 , F02C7/08 , F02C7/14 , F02C7/224 , F02C7/232 , F02C9/00 , F02C9/48 , F05D2220/32 , F05D2260/213 , G05B15/02 , G05D7/06 , Y02T50/675
摘要： A gas turbine engine according to an exemplary embodiment of this disclosure, among other possible things includes a fan. A geared architecture is configured for driving the fan. A turbine section is configured for driving the geared architecture. A thermal management system that includes a first fluid circuit and a second fluid circuit that manage heat generated in at least a portion of the gas turbine engine. A first heat exchanger is incorporated into each of the first fluid circuit and the second fluid circuit. A second heat exchanger is incorporated into the first fluid circuit. A valve controls an amount of a first fluid that is communicated to the first heat exchanger and the second heat exchanger. A controller is configured to control a positioning of the valve. The amount of the first fluid communicated to the first heat exchanger is based on a first characteristic of a second fluid and the amount of the first fluid communicated to the second heat exchanger is based on a second characteristic of the second fluid. A method and a system are also disclosed.
摘要翻译：根据本公开的示例性实施例的燃气涡轮发动机以及其它可能的事情包括风扇。齿轮架构配置为驱动风扇。涡轮机部分被配置用于驱动齿轮架构。一种热管理系统，其包括第一流体回路和第二流体回路，其管理在燃气涡轮发动机的至少一部分中产生的热量。第一热交换器被并入到第一流体回路和第二流体回路的每一个中。第二热交换器被并入到第一流体回路中。阀门控制与第一热交换器和第二热交换器连通的第一流体的量。控制器被配置为控制阀的定位。与第一热交换器连通的第一流体的量基于第二流体的第一特性，并且与第二热交换器连通的第一流体的量基于第二流体的第二特性。还公开了一种方法和系统。

4. 发明申请

US20140216003A1 GAS TURBINE ENGINE WITH GEARED TURBOFAN AND OIL THERMAL MANAGEMENT SYSTEM 审中-公开
标题翻译：燃气涡轮发动机与齿轮涡轮和油热管理系统
公开(公告)号：US20140216003A1
公开(公告)日：2014-08-07
申请号：US14245317
申请日：2014-04-04
申请人： UNITED TECHNOLOGIES CORPORATION
发明人： Kathleen R. Phillips , Thomas G. Phillips , Ethan K. Stearns , Federico Papa
IPC分类号： F01D25/20 , F02C7/06
CPC分类号： F01D25/20 , F01D25/18 , F01M5/002 , F02C7/06 , F02C7/14 , F02K9/64 , F05D2260/213 , F05D2260/40311 , Y02T50/676
摘要： A gas turbine engine includes a fan, a compressor section, a combustion section, and a turbine section. A fan drive gear system is configured for driving the fan at a speed different than the turbine section. A lubricant system includes a lubricant pump delivering lubricant to an outlet line. The outlet line splits into at least a hot line and into a cool line. The hot line is directed primarily to locations in the gas turbine engine that are not intended to receive cooler lubricant. The cool line is directed through one or more heat exchangers at which the lubricant is cooled, and the cool line then is routed to the fan drive gear system. At least one of the one or more heat exchangers is a fuel/oil cooler at which lubricant will be cooled by fuel leading to the combustion section. The fuel/oil cooler is downstream of a point where the outlet line splits into the at least the hot line and the cool line, such that the hot line is not directed through the fuel/oil cooler. A method is also disclosed.
摘要翻译：燃气涡轮发动机包括风扇，压缩机部，燃烧部和涡轮部。风扇驱动齿轮系统构造成以不同于涡轮部分的速度驱动风扇。润滑剂系统包括将润滑剂输送到出口管线的润滑剂泵。出口线分成至少一条热线，并进入冷线。热线主要针对燃气涡轮发动机中不用于接收较冷润滑剂的位置。冷却管线被引导通过一个或多个热交换器，在该热交换器处润滑剂被冷却，然后将冷却管线路由到风扇驱动齿轮系统。一个或多个热交换器中的至少一个是燃料/油冷却器，在该燃料/油冷却器处，通过燃料通向燃烧部分的润滑剂将被冷却。燃料/油冷却器在出口管线分成至少热管线和冷却管线的点的下游，使得热管线不被引导通过燃料/油冷却器。还公开了一种方法。

5. 发明申请

US20200300171A1 MODULATED FIRE EXTINGUISHING VENT FOR A GAS TURBINE ENGINE 审中-公开
公开(公告)号：US20200300171A1
公开(公告)日：2020-09-24
申请号：US16358760
申请日：2019-03-20
申请人： United Technologies Corporation
发明人： Nigel David Sawyers-Abbott , Federico Papa
IPC分类号： F02C7/25 , A62C3/08 , B64C7/02 , F02C9/18 , F02K3/04 , F02C9/34
摘要： A gas turbine engine includes an engine core having a compressor, a combustor fluidly connected to the compressor, and a turbine fluidly connected to the combustor. A core nacelle is disposed radially outward of the engine core. A cavity is disposed between an inner surface of the core nacelle and an outer surface of the engine core. The cavity includes a vent disposed at an aft end. The vent includes at least one flap configured to be maintained in an unrestricted position and in a restricted position. An actuator is configured to control the position of the at least one flap.

6. 发明申请

US20200208576A1 GAS TURBINE ENGINE AND METHOD TO COOL A GAS TURBINE ENGINE CASE ASSEMBLY 审中-公开
公开(公告)号：US20200208576A1
公开(公告)日：2020-07-02
申请号：US16812807
申请日：2020-03-09
申请人： United Technologies Corporation
发明人： Joseph D. Evetts , William J. Riordan , Federico Papa
IPC分类号： F02C7/12 , F02C9/18 , F02C3/04 , F01D25/24 , B64D29/00 , F02C6/08 , F02C7/18
摘要： A method of cooling a gas turbine engine case assembly includes moving a fan air valve that is operatively connected to a pre-cooler having a bypass inlet that is configured to receive bypass air that bypasses a gas turbine engine core to facilitate a provision of bypass air through a fan air valve inlet to the bypass inlet to a first open position, in response to a core compartment temperature being greater than a target core compartment temperature. The method further includes bleeding the bypass air through a bypass outlet of the pre-cooler into a core compartment.

7. 发明授权

US09334802B2 Gas turbine engine thermal management system 有权
标题翻译：燃气轮机发动机热管理系统
公开(公告)号：US09334802B2
公开(公告)日：2016-05-10
申请号：US13799406
申请日：2013-03-13
申请人： United Technologies Corporation
发明人： Federico Papa , Thomas G. Phillips , Kathleen R. Phillips , Ethan K. Stearns , Justin W. Heiss
IPC分类号： F02C7/12 , F01D25/12 , F02C7/08 , F02C7/14 , F02C9/00 , F02C3/08 , F02C7/06 , F02C7/224 , F02C7/232 , F02C9/48 , G05B15/02 , G05D7/06
CPC分类号： F02C7/12 , F01D25/12 , F02C3/08 , F02C7/06 , F02C7/08 , F02C7/14 , F02C7/224 , F02C7/232 , F02C9/00 , F02C9/48 , F05D2220/32 , F05D2260/213 , G05B15/02 , G05D7/06 , Y02T50/675
摘要： A thermal management system for a gas turbine engine according to an exemplary aspect of the present disclosure includes, among other things, a heat exchanger and a valve that controls an amount of a first fluid that is communicated through the heat exchanger A first sensor senses a first characteristic of a second fluid that is communicated through the heat exchanger to exchange heat with the first fluid and a second sensor senses a second characteristic of the second fluid. A positioning of the valve is based on at least one of the first characteristic and the second characteristic.
摘要翻译：根据本公开的示例性方面的用于燃气涡轮发动机的热管理系统尤其包括热交换器和阀，其控制通过热交换器A连通的第一流体的量第一传感器感测到第二流体的第一特征，其通过热交换器连通以与第一流体交换热量，第二传感器感测第二流体的第二特性。阀的定位基于第一特征和第二特性中的至少一个。

8. 发明授权

US09038397B2 Gas turbine engine thermal management system 有权
标题翻译：燃气轮机发动机热管理系统
公开(公告)号：US09038397B2
公开(公告)日：2015-05-26
申请号：US14247575
申请日：2014-04-08
申请人： United Technologies Corporation
发明人： Federico Papa , Thomas G. Phillips , Kathleen R. Phillips , Ethan K. Stearns , Justin W. Heiss
IPC分类号： F02C1/00 , F02C7/06 , F02K99/00 , F02C7/12 , F02C3/08 , F02C7/224 , F02C7/232 , F02C9/48 , G05B15/02 , G05D7/06
CPC分类号： F02C7/12 , F01D25/12 , F02C3/08 , F02C7/06 , F02C7/08 , F02C7/14 , F02C7/224 , F02C7/232 , F02C9/00 , F02C9/48 , F05D2220/32 , F05D2260/213 , G05B15/02 , G05D7/06 , Y02T50/675
摘要： A gas turbine engine according to an exemplary embodiment of this disclosure, among other possible things includes a fan. A geared architecture is configured for driving the fan. A turbine section is configured for driving the geared architecture. A thermal management system that includes a first fluid circuit and a second fluid circuit that manage heat generated in at least a portion of the gas turbine engine. A first heat exchanger is incorporated into each of the first fluid circuit and the second fluid circuit. A second heat exchanger is incorporated into the first fluid circuit. A valve controls an amount of a first fluid that is communicated to the first heat exchanger and the second heat exchanger. A controller is configured to control a positioning of the valve. The amount of the first fluid communicated to the first heat exchanger is based on a first characteristic of a second fluid and the amount of the first fluid communicated to the second heat exchanger is based on a second characteristic of the second fluid. A method and a system are also disclosed.
摘要翻译：根据本公开的示例性实施例的燃气涡轮发动机以及其它可能的事情包括风扇。齿轮架构配置为驱动风扇。涡轮机部分被配置用于驱动齿轮架构。一种热管理系统，其包括第一流体回路和第二流体回路，其管理在燃气涡轮发动机的至少一部分中产生的热量。第一热交换器被并入到第一流体回路和第二流体回路的每一个中。第二热交换器被并入到第一流体回路中。阀门控制与第一热交换器和第二热交换器连通的第一流体的量。控制器被配置为控制阀的定位。与第一热交换器连通的第一流体的量基于第二流体的第一特性，并且与第二热交换器连通的第一流体的量基于第二流体的第二特性。还公开了一种方法和系统。

9. 发明授权

US10619569B2 Gas turbine engine and method to cool a gas turbine engine case assembly 有权
公开(公告)号：US10619569B2
公开(公告)日：2020-04-14
申请号：US15185820
申请日：2016-06-17
申请人： United Technologies Corporation
发明人： Joseph D. Evetts , William J. Riordan , Federico Papa
IPC分类号： F02C7/12 , F02C7/18 , F02C6/08 , B64D29/00 , F01D25/24 , F02C3/04 , F02C9/18 , B64D13/08 , F01D11/24
CPC分类号： F02C7/12 , B64D29/00 , F01D25/24 , F02C3/04 , F02C6/08 , F02C7/18 , F02C9/18 , B64D13/08 , F01D11/24 , F02C7/185 , F05D2220/32 , F05D2260/20 , F05D2270/80 , Y02T50/675
摘要： A method of cooling a gas turbine engine case assembly includes moving a fan air valve that is operatively connected to a precooler having a bypass inlet that is configured to receive bypass air that bypasses a gas turbine engine core to facilitate a provision of bypass air through a fan air valve inlet to the bypass inlet to a first open position, in response to a core compartment temperature being greater than a target core compartment temperature. The method further includes bleeding the bypass air through a bypass outlet of the precooler into a core compartment.

10. 发明授权

US10443429B2 Gas turbine nacelle ventilation manifold having a circumferential varying cross-sectional area 有权
公开(公告)号：US10443429B2
公开(公告)日：2019-10-15
申请号：US15111553
申请日：2015-01-20
申请人： UNITED TECHNOLOGIES CORPORATION
发明人： Gabriel L. Suciu , Jesse M. Chandler , Federico Papa
IPC分类号： F02C7/18 , F01D17/14 , F01D25/26 , F02C3/04 , F02C9/18
摘要： A gas turbine engine comprises a core engine housing. A nacelle is positioned radially outwardly of the core engine housing. An outer bypass housing is positioned outwardly of the nacelle. There is at least one accessory to be cooled positioned in a chamber radially between the core engine housing and the nacelle. A manifold delivers cooling air into the chamber, and extends ng circumferentially about a central axis of the core engine. The nacelle has an asymmetric flow cross-section across a circumferential extent.

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