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1. 发明申请

US20180230908A1 HEAT EXCHANGER ASSEMBLY FOR A GAS TURBINE ENGINE PROPULSION SYSTEM 审中-公开
公开(公告)号：US20180230908A1
公开(公告)日：2018-08-16
申请号：US15398375
申请日：2017-01-04
申请人： Rolls-Royce North American Technologies, Inc. , Rolls-Royce Corporation
发明人： Kenneth M. Pesyna , Douglas J. Snyder , Patrick C. Sweeney
IPC分类号： F02C7/141 , F01D25/12 , F02C7/18 , B64D27/16 , B64D29/00 , F01D17/14 , B64D33/08 , B64D33/02
CPC分类号： F02C7/141 , B64D27/16 , B64D29/00 , B64D33/08 , B64D2033/024 , F01D17/145 , F01D25/12 , F02C7/14 , F02C7/185 , F02K3/115 , F05D2220/323 , F05D2260/213 , F05D2260/606 , Y02T50/675
摘要： A propulsion system including a gas turbine engine is disclosed herein. The propulsion system further includes a heat exchanger arranged outside the gas turbine engine and adapted to cool fluid from the gas turbine engine.

2. 发明申请

US20170089263A1 TURBINE ENGINE ADVANCED COOLING SYSTEM 审中-公开
公开(公告)号：US20170089263A1
公开(公告)日：2017-03-30
申请号：US14871382
申请日：2015-09-30
申请人： Rolls-Royce Corporation , Rolls-Royce North American Technologies Inc.
发明人： Joseph Clegg , Craig English , Behram Kapadia , Kenneth M. Pesyna , Jason Lee Swindle , Jason Wayne Rector , Christopher Vincent , Nicholas D. Metzger , Daniel G. Edwards
IPC分类号： F02C7/12 , F02C7/24 , F04D29/58 , F01D25/12 , F04D29/32 , F02C3/04 , F01D5/02
CPC分类号： F02C7/12 , F01D5/02 , F01D5/046 , F01D5/08 , F01D5/081 , F01D5/082 , F01D25/08 , F01D25/12 , F02C3/04 , F02C6/08 , F02C7/18 , F02C7/185 , F02C7/24 , F04D29/321 , F04D29/582 , F05D2220/32 , F05D2240/12 , F05D2240/15 , F05D2240/35 , F05D2240/60 , F05D2260/14 , F05D2260/20 , F05D2260/205 , F05D2260/231
摘要： A cooling system for a gas turbine is provided that may include a drive shaft, a shield of a combustor of the gas turbine engine, and a conduit. The drive shaft may be configured to mechanically couple a compressor of the gas turbine engine to a turbine of the gas turbine engine. The shield may be positioned between the compressor and the turbine. The combustor may be configured to drive the turbine. The conduit may be configured to supply a cooling fluid to a gap between an outer surface of the drive shaft and the shield of the combustor.

3. 发明授权

US12065965B1 Rotating detonation augmentors with adjustable throats for gas turbine engines 有权
公开(公告)号：US12065965B1
公开(公告)日：2024-08-20
申请号：US18234340
申请日：2023-08-15
申请人： Rolls-Royce North American Technologies Inc. , Rolls-Royce Corporation
发明人： Victor L. Oechsle , Kenneth M. Pesyna , Bryan H. Lerg , Michael C. Monzella , Zachary A. Rauch , Michael Moser
IPC分类号： F02K3/11 , F02C5/00 , F02K3/02 , F02K3/075 , F23R7/00
CPC分类号： F02C5/00 , F02K3/025 , F02K3/075 , F02K3/11 , F23R7/00
摘要： A gas turbine engine includes a bypass duct and a rotating detonation augmentor. The bypass duct is configured to conduct air through a flow path arranged around an engine core of the gas turbine engine to provide thrust for propelling the gas turbine engine. The rotating detonation augmentor is located in the bypass duct and configured to be selectively operated to detonate fuel and a portion of the air to increase the thrust for propelling the gas turbine engine.

4. 发明授权

US10208668B2 Turbine engine advanced cooling system 有权
公开(公告)号：US10208668B2
公开(公告)日：2019-02-19
申请号：US14871382
申请日：2015-09-30
申请人： Rolls-Royce Corporation , Rolls-Royce North American Technologies Inc.
发明人： Joseph Clegg , Craig English , Behram Kapadia , Kenneth M. Pesyna , Jason Lee Swindle , Jason Wayne Rector , Christopher Vincent , Nicholas D. Metzger , Daniel G. Edwards
IPC分类号： F02C7/12 , F01D5/08 , F01D25/08 , F02C7/18 , F01D5/04 , F01D5/02 , F01D25/12 , F02C3/04 , F02C7/24 , F04D29/32 , F04D29/58 , F02C6/08
摘要： A cooling system for a gas turbine is provided that may include a drive shaft, a shield of a combustor of the gas turbine engine, and a conduit. The drive shaft may be configured to mechanically couple a compressor of the gas turbine engine to a turbine of the gas turbine engine. The shield may be positioned between the compressor and the turbine. The combustor may be configured to drive the turbine. The conduit may be configured to supply a cooling fluid to a gap between an outer surface of the drive shaft and the shield of the combustor.

5. 发明授权

US10513981B2 Heat exchanger assembly for a gas turbine engine propulsion system 有权
公开(公告)号：US10513981B2
公开(公告)日：2019-12-24
申请号：US15398375
申请日：2017-01-04
申请人： Rolls-Royce North American Technologies, Inc. , Rolls-Royce Corporation
发明人： Kenneth M. Pesyna , Douglas J. Snyder , Patrick C. Sweeney
IPC分类号： F02C7/141 , F02C7/14 , F02K3/115 , B64D27/16 , B64D29/00 , B64D33/08 , F01D17/14 , F01D25/12 , F02C7/18 , B64D33/02
摘要： A propulsion system including a gas turbine engine is disclosed herein. The propulsion system further includes a heat exchanger arranged outside the gas turbine engine and adapted to cool fluid from the gas turbine engine.

6. 发明授权

US11339745B1 Dual flowpath exhaust for fuel cooling in a hypersonic propulsion system 有权
公开(公告)号：US11339745B1
公开(公告)日：2022-05-24
申请号：US16785056
申请日：2020-02-07
申请人： Rolls-Royce North American Technologies Inc.
发明人： Nicholas Metzger , Todd S. Taylor , Kenneth M. Pesyna , Timothy Roesler
IPC分类号： F02K1/82 , F02K7/16 , F02C7/224 , B64D33/04 , F02K1/06 , F02C7/04
摘要： A dual flow path exhaust assembly for use with a combined turbofan and ramjet engine includes a turbofan engine exhaust duct, a ramjet engine exhaust duct, a combined outlet, and door configured to move between an open position and a closed position to selectively isolate the turbofan engine exhaust duct from the combined outlet.

7. 发明授权

US10544755B2 Variable infrared suppression system in a gas turbine engine 有权
公开(公告)号：US10544755B2
公开(公告)日：2020-01-28
申请号：US15270903
申请日：2016-09-20
申请人： Rolls-Royce North American Technologies, Inc.
发明人： Kenneth M. Pesyna , Anthony F. Pierluissi
IPC分类号： F02K1/48 , F02K1/82 , F02K1/12 , B64D33/04
摘要： According to one aspect, an infrared suppression system that utilizes a primary airflow and a secondary air flow for a gas turbine engine is provided. The infrared suppression system includes an exit flap configured to control a flow of exhaust air out of the gas turbine engine and a secondary flow door that is configured to selectively control the secondary air flow into the gas turbine engine. The mixture of the secondary air flow and the primary air flow from the gas turbine engine suppresses an infrared signature produced by the gas turbine engine.

8. 发明授权

US09840967B2 Ram air thermal management system 有权
公开(公告)号：US09840967B2
公开(公告)日：2017-12-12
申请号：US14132716
申请日：2013-12-18
申请人： Rolls-Royce North American Technologies, Inc.
发明人： Douglas J. Snyder , Kenneth M. Pesyna
IPC分类号： F01N5/02 , F02C7/18 , F02K3/115 , F02C7/14
CPC分类号： F02C7/185 , F02C7/14 , F02K3/115 , F05D2260/601 , Y02T50/671 , Y02T50/675
摘要： An aircraft may have a heat generating component and an engine, at least one of which generates a heat load, and a thermal management system to cool the heat load. The engine may have a duct and an engine fan configured to draw an inlet air stream into an inlet portion of the duct, where at least a portion of the inlet air stream may be used as an engine air stream. The thermal management system may include a cooling circuit configured to circulate a fluid through the heat load such that at least a portion of it may be transferred to the fluid, a heat exchanger configured to enable heat transfer between the fluid and a cooling air stream, and a pumping device. The pumping device may be configured to draw the cooling air stream through the heat exchanger and into a portion of the engine air stream.

9. 发明授权

US09464594B2 Compact actuation system for flow nozzle 有权
标题翻译：紧凑的流动喷嘴致动系统
公开(公告)号：US09464594B2
公开(公告)日：2016-10-11
申请号：US14209749
申请日：2014-03-13
申请人： Rolls-Royce North American Technologies, Inc.
发明人： Kenneth M. Pesyna
IPC分类号： F02K1/12 , F02K1/15 , F02K3/075 , F02K3/077 , F02K3/115 , F02K1/80
CPC分类号： F02K1/1223 , F02K1/1207 , F02K1/1238 , F02K1/15 , F02K1/80 , F02K3/075 , F02K3/077 , F02K3/115 , F05D2250/411 , F05D2260/50 , F05D2260/56 , F05D2270/051 , F05D2270/66 , Y02T50/671
摘要： Embodiments may include an actuation system for an exhaust nozzle of a gas turbine engine. The actuation system may comprise a plurality of flap assemblies including a plurality of convergent flaps movable between first and second convergent positions and a plurality of divergent flaps movable between first and second divergent positions. Each of the plurality of divergent flaps may extend from a respective one of the plurality of convergent flaps. The system may further include a first sync ring rotatably carried by an engine body and configured to synchronously move the divergent flaps between the first and second divergent positions and a second sync ring rotatably carried by the engine body and configured to synchronously move the convergent flaps between the first and second convergent positions. A method may translate rotation of the sync ring to movement of a vehicle surface between radially outward and inward positions.
摘要翻译：实施例可以包括用于燃气涡轮发动机的排气喷嘴的致动系统。致动系统可以包括多个翼片组件，其包括可在第一和第二收敛位置之间移动的多个收敛翼片和可在第一和第二发散位置之间移动的多个发散翼片。多个发散片中的每一个可以从多个收敛片中的相应一个延伸。该系统可以进一步包括第一同步环，该第一同步环由发动机本体可旋转地承载并且构造成在第一和第二发散位置之间同步地移动发散翼片，以及第二同步环，该第二同步环由发动机主体可转动地支撑并且构造成使收敛翼片在第一和第二收敛位置。一种方法可以将同步环的旋转转移到径向向外和向内位置之间的车辆表面的移动。

10. 发明申请

US20140271116A1 HEAT EXCHANGER INTEGRATED WITH A GAS TURBINE ENGINE AND ADAPTIVE FLOW CONTROL 有权
标题翻译：热交换器与气体涡轮发动机和自适应流量控制集成
公开(公告)号：US20140271116A1
公开(公告)日：2014-09-18
申请号：US14107412
申请日：2013-12-16
申请人： Rolls-Royce North American Technologies, Inc.
发明人： Douglas J. Snyder , Kenneth M. Pesyna , Anthony F. Pierluissi
IPC分类号： F02C7/12
CPC分类号： F02C7/12 , F01D25/12 , F02C7/14 , F02C7/141 , F02C7/18 , F02K3/06 , F05D2260/20 , Y02T50/675
摘要： One embodiment of an engine may include an enclosure surrounding an engine having an engine centerline, and the enclosure defining a passage for a cold-side airflow. The engine may also include one or more contiguous heat exchangers having a cold side inlet surface receiving a cold-side airflow. The heat exchanger may be disposed within the passage, such that a surface normal relative to the cold side inlet surface is offset by at least 30 degrees from the engine centerline.
摘要翻译：发动机的一个实施例可以包括围绕具有发动机中心线的发动机的外壳，并且外壳限定用于冷侧气流的通道。发动机还可以包括一个或多个连续的热交换器，其具有接收冷侧气流的冷侧入口表面。热交换器可以设置在通道内，使得相对于冷侧入口表面法线的表面与发动机中心线相抵离至少30度。

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