专利快速检索-快速检索全球专利，免费商用专利数据库-IPRDB

81. 发明授权

US09884688B2 Propulsion system using large scale vortex generators for flow redistribution and supersonic aircraft equipped with the propulsion system 有权
公开(公告)号：US09884688B2
公开(公告)日：2018-02-06
申请号：US14172560
申请日：2014-02-04
申请人： Gulfstream Aerospace Corporation
发明人： Michael Rybalko , Timothy R. Conners , Thomas R. Wayman
IPC分类号： B64D29/00 , B64D27/00 , B64D33/02 , F02K7/10 , F02K3/02 , B64C30/00 , B64D27/02
CPC分类号： B64D29/00 , B64C30/00 , B64D27/00 , B64D27/02 , B64D33/02 , B64D2033/0226 , B64D2033/026 , F02K3/025 , F02K7/10 , F05D2210/33 , F05D2220/10 , Y02T50/671
摘要： A propulsion system for a supersonic aircraft includes an engine including an engine core and an engine bypass, a compression surface upstream of the engine, a shroud surrounding the engine configured to direct airflow passing over the compression surface towards the engine, and a plurality of vortex generators positioned upstream of the engine. The vortex generators have a height such that when the supersonic aircraft is flown at a predetermined altitude and predetermined speed, the plurality of vortex generators create vortices that propagate partially outside of a boundary layer formed proximate a surface of a supersonic inlet. The vortices cause a high-velocity portion of the airflow to move towards the engine core and a low-velocity portion of the airflow to move towards the engine bypass. The plurality of vortex generators are disposed aft of a terminal shock and have a height greater than the thickness of the boundary layer.

82. 发明授权

US09862498B2 Laser-charged high-speed propulsion system and method for production of high-powered laser 有权
公开(公告)号：US09862498B2
公开(公告)日：2018-01-09
申请号：US14326043
申请日：2014-07-08
申请人： Byron Wells , Matthias Ihme
发明人： Byron Wells , Matthias Ihme
IPC分类号： B64D33/02 , F02C7/264 , B64C30/00 , F02C3/04 , F02K7/14 , F02C3/14 , F23R3/00 , B64D33/04
CPC分类号： B64D33/02 , B64C30/00 , B64D33/04 , B64D2033/026 , F02C3/04 , F02C3/14 , F02C7/264 , F02K7/14 , F05D2220/10 , F23R3/00 , F23R2900/00006
摘要： A high-speed propulsion system for a high-speed vehicle includes an air intake duct, a compression section, a combustion section, and an expansion section. A gas dynamic laser generator is disposed proximate the expansion section and generates a source of laser light. A laser transmission mechanism receives the laser light and transmits the laser light from the gas dynamic laser generator to the combustion section and to presents the laser light into the air/fuel mixture of the flowpath which promotes mixing, combustion, and flame stability.

83. 发明申请

US20170234240A1 INLET TURBINE AND TRANSMISSION FOR HIGH-MACH ENGINES 审中-公开
公开(公告)号：US20170234240A1
公开(公告)日：2017-08-17
申请号：US15418186
申请日：2017-01-27
申请人： Rolls-Royce North American Technologies, Inc.
发明人： Douglas D. Dierksmeier , Edward C. Rice , Steven W. Tomlinson , Bradley E. Auker , Donald Klemen
IPC分类号： F02C9/18 , B64D27/10 , F02C7/36 , F02C3/04 , F02K3/06
CPC分类号： F02C9/18 , B64C30/00 , B64D27/10 , B64D33/02 , B64D2033/026 , F02C3/107 , F02C7/36 , F05D2220/80 , F05D2270/304
摘要： A high-Mach engine includes a gas turbine core, an inlet assembly, and a transmission. The inlet assembly including an inlet turbine and the transmission configured to couple the inlet turbine and a core turbine of the gas turbine core cooperate to control air moving through the high-Mach engine.

84. 发明申请

US20160288917A1 VARIABLE-CAPTURE SUPERSONIC INLET 有权
标题翻译：可变接收超级入口
公开(公告)号：US20160288917A1
公开(公告)日：2016-10-06
申请号：US14674170
申请日：2015-03-31
申请人： The Boeing Company
发明人： Thuy Huynh , David J. Wilson
IPC分类号： B64D33/02 , B64C1/00 , F02C7/042
CPC分类号： B64D33/02 , B64C1/0009 , B64D2033/026 , F02C7/042
摘要： An engine inlet for efficient operation at both design Mach number and off-design Mach numbers has a fixed compression surface and a leading edge that is variably extendible over the fixed compression surface to simultaneously vary capture area, compression and shock wave position.
摘要翻译：在设计马赫数和非设计马赫数两种情况下都能有效运行的发动机进气口具有固定的压缩表面和在固定压缩表面上可变地延伸的前缘，以同时改变捕获面积，压缩和冲击波位置。

85. 发明申请

US20150315971A1 HIGH-SPEED VEHICLE POWER AND THERMAL MANAGEMENT SYSTEM AND METHODS OF USE THEREFOR 审中-公开
标题翻译：高速车辆动力和热管理系统及其使用方法
公开(公告)号：US20150315971A1
公开(公告)日：2015-11-05
申请号：US14519872
申请日：2014-10-21
申请人： Government of the United States as Represented by the Secretary of the Air Force
发明人： Thomas L. Reitz , Larry Byrd
IPC分类号： F02C7/224 , B64D33/08 , B64C30/00
CPC分类号： B64C30/00 , B64C1/38 , B64D33/08 , B64D37/34 , B64D2033/024 , B64D2033/026 , F01K15/02 , F02C7/224 , F02C7/236 , F02K1/822 , F05D2220/323 , F05D2220/62 , F05D2220/76 , F05D2220/80 , F05D2260/601 , F05D2300/514 , Y02T50/675 , Y02T90/44
摘要： A thermal management and power generation system for a hypersonic vehicle. The thermal management and power generation system comprising a fluid supply having a volatile fluid and a fuel supply having an endothermic fuel. A first heat exchanger, fluidically coupled to the fluid supply, absorbs heat from a first portion of the hypersonic vehicle, which vaporizes the volatile fluid. A mixing apparatus, fluidically coupled to the first heat exchanger and the fuel supply combines the vaporized volatile fuel and endothermic fuel. A second heat exchanger, fluidically coupled to the mixing apparatus, absorbs heat from a second portion of the hypersonic vehicle and decomposes the endothermic fuel by endothermic pyrolysis. A heat engine, fluidically coupled to the first heat exchanger and the mixing apparatus, is configured to generate an electrical power for use by the hypersonic vehicle. The vaporized volatile fluid mixed with the endothermic fuel within the second heat exchanger reduces coking caused by the endothermic pyrolytic decomposition of the endothermic fuel as compared to an endothermic pyrolytic decomposition of an endothermic fuel not having a vaporized volatile fluid mixed therewith.
摘要翻译：用于超音速车辆的热管理和发电系统。热管理和发电系统包括具有挥发性流体的液体供应源和具有吸热燃料的燃料供应。流体耦合到流体供应源的第一热交换器从超音速车辆的第一部分吸收热量，其使挥发性流体蒸发。流体耦合到第一热交换器和燃料供应的混合装置将蒸发的挥发性燃料和吸热燃料组合。流体耦合到混合装置的第二热交换器从超音速车辆的第二部分吸收热量并通过吸热裂解分解吸热燃料。流体耦合到第一热交换器和混合装置的热引擎被配置为产生用于超音速车辆的电力。与第一热交换器中的吸热燃料混合的蒸发的挥发性流体与吸热燃料的吸热热分解相比，减少了由吸热燃料的吸热热分解引起的焦化，该吸热燃料不具有与其混合的蒸发的挥发性流体。

86. 发明授权

US09121369B2 Nozzle arrangement and method of making the same 有权
标题翻译：喷嘴布置和制作方法
公开(公告)号：US09121369B2
公开(公告)日：2015-09-01
申请号：US13541495
申请日：2012-07-03
申请人： Timothy R. Conners , Preston A. Henne , Donald C. Howe
发明人： Timothy R. Conners , Preston A. Henne , Donald C. Howe
IPC分类号： F02K1/46 , F02K1/04 , B64D33/02 , F02K3/02 , F02C7/04
CPC分类号： F02K1/46 , B64D33/02 , B64D2033/026 , B64D2033/0273 , B64D2033/0286 , F02C7/00 , F02C7/04 , F02C7/045 , F02K1/04 , F02K1/34 , F02K3/02 , F02K7/00 , F02K7/10 , F02K7/16 , F02K7/20 , F05D2210/12 , F05D2220/323 , F05D2220/80 , F05D2230/60 , F05D2250/70 , F05D2260/96 , Y10T29/49346 , Y10T137/0536
摘要： A nozzle arrangement is disclosed herein for use with a supersonic jet engine that is configured to produce a plume of exhaust gases. The nozzle arrangement includes, but is not limited to, a nozzle having a trailing edge and a plug body partially positioned within the nozzle. The plug body has an expansion surface and a compression surface downstream of the expansion surface. A protruding portion of the plug body extends downstream of the trailing edge for a length greater than a conventional plug body length. The plug body is configured to shape the exhaust gases to flow substantially parallel to a free stream of air flowing off of the trailing edge of the nozzle and to cause the plume of exhaust gases to isentropically turn the free stream of air to move in a direction parallel to a longitudinal axis of the plug body.
摘要翻译：本文公开了一种用于与超音速喷气发动机一起使用的喷嘴装置，其构造成产生一排废气。喷嘴装置包括但不限于具有后缘和部分地位于喷嘴内的塞体的喷嘴。塞体具有膨胀表面和膨胀表面下游的压缩表面。插塞体的突出部分在后缘的下游延伸长度大于常规的塞体长度。塞体构造成使废气成形为基本上平行于从喷嘴的后缘流出的自由空气流流动，并且使排气的羽流等速转动空气的自由流沿着方向平行于插头主体的纵向轴线。

87. 发明授权

US09027583B2 Low shock strength inlet 有权
标题翻译：低冲击强度入口
公开(公告)号：US09027583B2
公开(公告)日：2015-05-12
申请号：US13705211
申请日：2012-12-05
申请人： Gulfstream Aerospace Corporation
发明人： Timothy R. Conners
IPC分类号： F02B27/00 , F02C7/042 , B64D33/02 , F02C7/045
CPC分类号： B64D33/02 , B64D29/00 , B64D33/06 , B64D2033/026 , B64D2033/0273 , F02C7/042 , F02C7/045 , F02K3/025 , F02K7/16 , F05D2220/80 , Y02T50/672 , Y10T137/0368 , Y10T137/0536
摘要： A supersonic inlet having a cowl lip configured to capture the conic shock and exhibit a zero or substantially zero cowl angle is disclosed herein. The inlet may be configured to employ a relaxed isentropic compression surface and an internal bypass. The nacelle bypass may prevent flow distortions, introduced by the capture of the conic shock, from reaching the turbomachinery, thereby allowing the cowl angle to be reduced to zero or substantially zero. Such a cowl angle may reduce the inlet's contribution to the overall sonic boom signature for a supersonic aircraft while allowing for an increase in engine pressure recovery and a subsequent improvement in generated thrust by the engine.
摘要翻译：本文公开了一种超音速入口，其具有配置成捕获圆锥冲击并且呈现零或基本上零前角的整流罩。入口可以被配置为采用松弛的等熵压缩表面和内部旁路。机舱旁路可以防止由锥形冲击的捕获引入的流动变形到达涡轮机械，从而允许前导角减小到零或基本为零。这样的前导角度可以减小入口对超音速飞行器的整体声波爆震特征的贡献，同时允许发动机压力恢复增加，并随后改善发动机产生的推力。

88. 发明授权

US08973370B2 Low shock strength propulsion system 有权
标题翻译：低冲击强度推进系统
公开(公告)号：US08973370B2
公开(公告)日：2015-03-10
申请号：US14304524
申请日：2014-06-13
申请人： Gulfstream Aerospace Corporation
发明人： Timothy R. Conners
IPC分类号： F02K7/08 , F02K99/00 , F02B27/00 , B64D33/02 , F02K1/34 , B64D29/00 , F02K3/02
CPC分类号： B64D33/02 , B64D29/00 , B64D33/06 , B64D2033/026 , B64D2033/0273 , F02C7/042 , F02C7/045 , F02K3/025 , F02K7/16 , F05D2220/80 , Y02T50/672 , Y10T137/0368 , Y10T137/0536
摘要： A supersonic nacelle design employing a bypass flow path internal to the nacelle and around the engine is disclosed herein. A set of aerodynamic vanes may be used to shape a supersonic airflow within a bypass around an engine. The vanes may be capable of compressing the supersonic airflow into a subsonic airflow, direct the subsonic airflow around the engine, and then expand the subsonic airflow into a supersonic exhaust. The vanes may shape the airflow by reducing sonic boom strength, cowl drag, and airframe interference drag.
摘要翻译：本文公开了采用在机舱内部和发动机周围的旁通流路的超音速机舱设计。一组空气动力叶片可用于在发动机周围的旁路内形成超音速气流。叶片可能能够将超音速气流压缩成亚音速气流，引导发动机周围的亚音速气流，然后将亚音速气流膨胀成超音速排气。叶片可以通过降低声音臂强度，整流罩拖动和机身干涉阻力来形成气流。

89. 发明申请

US20150013305A1 Dual-Mode Combustor 有权
标题翻译：双模式燃烧器
公开(公告)号：US20150013305A1
公开(公告)日：2015-01-15
申请号：US13941987
申请日：2013-07-15
申请人： U.S.A. as represented by the Administrator of the National Aeronautics and Space Administration
发明人： Charles J. Trefny , Vance F. Dippold
IPC分类号： F02K7/14 , F02K7/10
CPC分类号： F02K7/14 , B64D2033/026 , F02K7/10 , F23R3/16 , F23R3/18 , F23R3/42 , Y02T50/671
摘要： A new dual-mode ramjet combustor used for operation over a wide flight Mach number range is described. Subsonic combustion mode is usable to lower flight Mach numbers than current dual-mode scramjets. High speed mode is characterized by supersonic combustion in a free-jet that traverses the subsonic combustion chamber to a variable nozzle throat. Although a variable combustor exit aperture is required, the need for fuel staging to accommodate the combustion process is eliminated. Local heating from shock-boundary-layer interactions on combustor walls is also eliminated.
摘要翻译：描述了一种用于在宽飞行马赫数范围内操作的新型双模式冲压喷气式燃烧器。亚音速燃烧模式可用于降低飞行马赫数，而不是当前的双模式切换。高速模式的特征在于通过将亚音速燃烧室穿过可变喷嘴喉部的自由射流中的超音速燃烧。虽然需要可变的燃烧器出口孔，但是消除了燃料分级以适应燃烧过程的需要。也消除了在燃烧器壁上的冲击边界层相互作用的局部加热。

90. 发明授权

US08590842B2 Tailorable stiffness shape morphing flow-path 有权
标题翻译：可塑刚度形状变形流动路径
公开(公告)号：US08590842B2
公开(公告)日：2013-11-26
申请号：US12406644
申请日：2009-03-18
申请人： Sergio L. dos Santos e Lucato , David B. Marshall , Daniel Edward Driemeyer
发明人： Sergio L. dos Santos e Lucato , David B. Marshall , Daniel Edward Driemeyer
IPC分类号： B64C13/16
CPC分类号： F02C7/042 , B64D33/02 , B64D2033/026 , Y02T50/67 , Y02T50/672 , Y10T29/494 , Y10T137/0318 , Y10T137/0536
摘要： An apparatus and method for an improved morphing flow path. A flexible structure has a plurality of sections which include a first section and a second section. An actuator system is connected to the flexible structure and includes a number of actuators. The actuator system is capable of changing a configuration of the flexible structure. A controller is connected to the actuator system. The controller is capable of changing a position of a number of actuators within the actuator system.
摘要翻译：一种用于改进变形流动路径的装置和方法。柔性结构具有包括第一部分和第二部分的多个部分。致动器系统连接到柔性结构并且包括多个致动器。致动器系统能够改变柔性结构的构造。控制器连接到执行器系统。控制器能够改变致动器系统内的多个致动器的位置。

你已经成功收藏专利！

检索式保存成功!

IPRDB

热门服务

关于我们

友情链接

联系方式