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1. 发明公开

US20240287952A1 ENGINE WITH ROTATING DETONATION COMBUSTION SYSTEM 审中-公开
公开(公告)号：US20240287952A1
公开(公告)日：2024-08-29
申请号：US18643376
申请日：2024-04-23
申请人： General Electric Company
发明人： Sibtosh Pal , Steven Clayton Vise , Arthur Wesley Johnson , Clayton Stuart Cooper , Joseph Zelina
IPC分类号： F02K7/10 , F02K7/02 , F02K7/08 , F02K7/16 , F23R3/18 , F23R3/34 , F23R7/00
CPC分类号： F02K7/10 , F02K7/02 , F02K7/08 , F02K7/16 , F23R7/00 , F05D2220/10 , F05D2250/90 , F23R3/18 , F23R3/34
摘要： A Brayton cycle engine and method for operation. The engine includes an inner wall assembly and an upstream wall assembly each extended from a longitudinal wall into a gas flowpath. An actuator adjusts a depth of the detonation combustion region into the gas flowpath between the inner wall assembly and the upstream wall assembly. The engine flows an oxidizer through the gas flowpath and the inner wall captures a portion of the oxidizer. The engine further adjusts the captured flow of oxidizer via the upstream wall and flows a first flow of fuel to the captured flow of oxidizer to produce rotating detonation gases. The engine flows the detonation gases downstream and to mix with the flow of oxidizer, and flows and burns a second flow of fuel to the detonation gases/oxidizer mixture to produce thrust.

2. 发明公开

US20240133352A1 Duplex Turbine Guide Vane Assembly 审中-公开
公开(公告)号：US20240133352A1
公开(公告)日：2024-04-25
申请号：US18377983
申请日：2023-10-08
申请人： ATRX, Inc.
发明人： John A Bossard , John L Bergmans
IPC分类号： F02K7/16 , F01D9/04 , F02K3/10 , F02K3/12 , F02K7/18 , F02K9/08 , F02K9/26 , F02K9/30 , F02K9/42 , F02K9/48 , F02K9/76 , F02K9/78 , F02K9/97
CPC分类号： F02K7/16 , F01D9/041 , F02K3/10 , F02K3/12 , F02K7/18 , F02K9/08 , F02K9/26 , F02K9/30 , F02K9/42 , F02K9/48 , F02K9/76 , F02K9/78 , F02K9/97 , F05D2220/74 , F05D2240/128 , F05D2240/35
摘要： A Duplex Turbine Guide Vane (DTGV) assembly for a turbojet engine includes DTGVs arranged on a non-rotating guide vane ring configured to be positioned coaxially in apposition with a rotatable turbine wheel comprising turbine blades. Each of the DTGVs has an internal channel configured for receiving a gas and delivering the gas toward the turbine blades.

3. 发明申请

US20220090560A1 HELICON YIELD PLASMA ELECTROMAGNETIC RAM-SCRAMJET DRIVE ROCKET ION VECTOR ENGINE 有权
公开(公告)号：US20220090560A1
公开(公告)日：2022-03-24
申请号：US17368589
申请日：2021-07-06
申请人： Sonic Blue Aerospace, Inc.
发明人： Richard H. Lugg
IPC分类号： F02K7/14 , F02K7/18 , F02K7/16 , F03H1/00
摘要： HYPERDRIVE receives continuous air breathing assistance from compressed atmospheric air through a high speed magnetically core driven turbine accelerator which resolves around a common flow path tunnel. The tunnel runs from the front to the back of the engine. It is assisted by a series of radial geometric ramjet engines that share the common flow path tunnel for hypersonic exhaust but has separate inlet air from a linear aerospike which governs mass flow of air, velocity of inlet air and pressure to the turbine and/or ramjets, as well as the positioning of the shock wave at the inlet to reduce aerodynamic drag. The ramjet is of hybrid engine design where it can also function as a scramjet, thus a ram-scramjet structure for combustion in a radial configuration about the engine (aft of an electrical compressor), where the common flow path tunnel also serves as a compression tunnel to compress air through a the constantly occurring series of compression shocks entering from and around the aerospike.

4. 发明授权

US11261791B2 Hybrid propulsion cooling system 有权
公开(公告)号：US11261791B2
公开(公告)日：2022-03-01
申请号：US16284823
申请日：2019-02-25
申请人： Rolls-Royce Corporation
发明人： Robert T. Duge
IPC分类号： F02C7/12 , F02C7/18 , F02C6/16 , F02K3/02 , F02K7/14 , F02K7/16 , F01D25/14 , F01D25/26
摘要： A hybrid propulsion system is provided. The system may comprise a gas turbine engine and a secondary engine, an inlet, an exhaust, a pressurized tank, and an expansion valve. The inlet may be in fluid communication with the ambient environment. The gas turbine engine may have a core passage including a compressor, a combustion chamber, and a turbine. The core passage may be in selective fluid communication with the inlet. The exhaust may be in fluid communication with the ambient environment and the core passage. The pressurized tank may be located upstream of the core passage. The pressurized tank may contain a cooling fluid. The expansion valve may be in fluid communication with the pressurized tank and the core passage. The pressurized tank may provide cooling fluid to the core passage to cool the gas turbine engine during operation of the secondary engine.

5. 发明申请

US20210324817A1 Supersonic Turbofan Engine 有权
公开(公告)号：US20210324817A1
公开(公告)日：2021-10-21
申请号：US17357577
申请日：2021-06-24
申请人： Sarah Qureshi , Masood Latif Qureshi
发明人： Sarah Qureshi , Masood Latif Qureshi
IPC分类号： F02K7/16 , F02K3/04 , F02C6/20
摘要： A gas turbine engine designed to take-off and land as a conventional turbofan engine at subsonic speeds and accelerate to supersonic speeds during flight by converting into a hybrid turbojet and ramjet engine. This is achieved by introducing an afterburner in the bypass duct of the engine and by retracting the bypass fan backward into a cylinder. This operation is carried out before the aircraft enters the transonic regime, at any stage below Mach 1. At supersonic speed, the shock wave is deflected through a needle cone that is projected out of the nose of the engine in order to prevent the intake air from being choked.

6. 发明授权

US11060484B2 Nozzle wall for an air-breathing engine of a vehicle and method therefor 有权
公开(公告)号：US11060484B2
公开(公告)日：2021-07-13
申请号：US16023411
申请日：2018-06-29
申请人： The Boeing Company
发明人： Joseph S. Silkey , Timothy H. Franklin , Richard S. Dyer
IPC分类号： F02K9/97 , B64D33/02 , F02C7/057 , F02K7/16
摘要： A nozzle wall for an air-breathing engine, the nozzle wall including a first wall surface subject to engine exhaust flow, a nozzle cooling system including at least one heat exchange fluid passage disposed adjacent the first wall surface so as to increase a temperature of a cooling fluid flowing from a fluid reservoir to at least a power extraction device, and the cooling fluid is ejected from the nozzle cooling system downstream from the power extraction device.

7. 发明授权

US11041463B1 Turbine engine structure with oxidizer enhanced mode 有权
公开(公告)号：US11041463B1
公开(公告)日：2021-06-22
申请号：US14619382
申请日：2015-02-11
申请人： United Technologies Corporation
发明人： Carl F. Weiss
IPC分类号： F02K7/16 , F02K3/06 , F02K3/11 , F02C7/268 , F02K3/04
摘要： A turbine engine structure includes a turbine engine core having a core cocooning feature, and a fan fore of the turbine engine core, relative to fluid flow through the turbine engine structure. The fan is drivably connected to the turbine engine core via a shaft. A nacelle circumferentially surrounds the turbine engine core, and a bypass flowpath is defined between the turbine engine core and the nacelle. A plurality of augmenter fuel spray bars are disposed in the bypass flowpath.

8. 发明申请

US20190234308A1 HIGH-MACH VEHICLE COOLING 审中-公开
公开(公告)号：US20190234308A1
公开(公告)日：2019-08-01
申请号：US15882463
申请日：2018-01-29
申请人： Rolls-Royce North American Technologies Inc.
发明人： Douglas D. Dierksmeier
IPC分类号： F02C7/14 , F02K7/16 , F01D15/10 , F02C9/16 , B64D13/08 , F25B11/02
摘要： Vehicles, such as aircraft, may include turbine-based combined cycle power plants (TBCC) for power to achieve high-mach speeds. Cooling systems for such TBCC may include a turbine-generator arranged to be driven for rotation by ambient air to reduce the temperature of the ambient air while providing electric power for use under cocooning of a primary gas turbine engine in favor of a scramjet engine during high-mach travel.

9. 发明授权

US10173784B2 Mobile multi-mode power generation system with mode based adjustable drag configuration 有权
公开(公告)号：US10173784B2
公开(公告)日：2019-01-08
申请号：US15132300
申请日：2016-04-19
申请人： The United States of America as represented by the Secretary of the Navy
发明人： James Stewart , Lyndon P. McCoy , Gerald Miller
IPC分类号： B64D41/00 , F02C7/042 , F02C7/36 , B64D27/12 , F02K7/10 , F02K7/16
摘要： Various embodiments of the invention can include a portable power system with multiple power generation modes and mode based adjustable drag configuration. Embodiments of the invention include a system with an adjustable inlet ram air inlet, a ram air powered section (e.g. a ram air powered turbine with an adjustable ram air inlet), a fuel powered section, e.g., jet fuel powered auxiliary power unit, which is used when insufficient ram air is present or a power surge requires augmented power generation, and a generator section selectively coupled with the ram air powered section and the fuel powered section.

10. 发明授权

US07828243B2 SCRAMjet arrangement for hypersonic aircraft 有权
标题翻译：用于超音速飞机的SCRAM喷射装置
公开(公告)号：US07828243B2
公开(公告)日：2010-11-09
申请号：US11196187
申请日：2005-08-03
申请人： Allen A. Arata
发明人： Allen A. Arata
IPC分类号： F02K7/10 , F02K7/16 , B64D27/16
CPC分类号： F02K7/14 , F02C6/00 , F02K7/16 , F05D2220/80
摘要： Hypersonic aircraft having a lateral arrangement of turbojet and SCRAMjet engines are disclosed. The SCRAMjet engines may be positioned laterally outboard of the turbojet engines. In one embodiment, the turbojet inlet and outlet openings may be covered during use of the SCRAMjets in order to provide compression and expansion ramps for the laterally adjacent SCRAMjet engines. The side-by-side arrangement of the turbojet and SCRAMjet engines reduces the vertical thickness of the aircraft, thereby reducing drag and potentially increasing performance.
摘要翻译：公开了具有涡轮喷气发动机和SCRAM喷射发动机的横向布置的超音速飞机。 SCRAMjet发动机可以横向位于涡轮喷气发动机外侧。在一个实施例中，涡轮喷气发动机入口和出口开口可以在SCRAM喷射器的使用期间被覆盖，以便为侧向相邻的SCRAM喷射发动机提供压缩和膨胀斜坡。涡轮喷气发动机和SCRAM喷气发动机的并排布置降低了飞机的垂直厚度，从而减少了阻力并且潜在地提高了性能。

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