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51. 发明授权

US06883330B2 Variable geometry inlet design for scram jet engine 失效
标题翻译：用于冲击式发动机的可变几何入口设计
公开(公告)号：US06883330B2
公开(公告)日：2005-04-26
申请号：US10264172
申请日：2002-10-02
申请人： Daniel P. Guinan , Alan Drake , Dean Andreadis , Stephen A. Beckel
发明人： Daniel P. Guinan , Alan Drake , Dean Andreadis , Stephen A. Beckel
IPC分类号： F02C7/042 , F02K7/14 , F02K7/08
CPC分类号： F02K7/14
摘要： The present invention relates to an improved variable geometry inlet for a scram jet engine having at least one combustor module. The variable geometry inlet comprises each combustor module having two sidewalls. Each of the sidewalls has a central portion with a thickness and a tapered profile forward of the central portion. The tapered profile terminates in a sharp leading edge. The variable geometry inlet further comprises each module having a lower wall and a movable cowl flap positioned forward of the lower wall. The movable cowl flap has a leading edge and the leading edges of the sidewalls intersect the leading edge of the cowl flap.
摘要翻译：本发明涉及一种用于具有至少一个燃烧器模块的冲击式发动机的改进的可变几何入口。可变几何入口包括具有两个侧壁的每个燃烧器模块。每个侧壁具有中心部分，该中心部分具有中心部分的前方的厚度和锥形轮廓。锥形轮廓终止于锋利的前缘。可变几何形状入口还包括每个模块，其具有位于下壁前方的下壁和可移动整流罩。可移动整流罩具有前缘，并且侧壁的前缘与整流罩的前缘相交。

52. 发明授权

US06532728B1 Reducing skin friction drag 失效
标题翻译：降低皮肤摩擦阻力
公开(公告)号：US06532728B1
公开(公告)日：2003-03-18
申请号：US09693586
申请日：2000-10-20
申请人： Christopher Paul Goyne , Raymond John Stalker , Allan Paull
发明人： Christopher Paul Goyne , Raymond John Stalker , Allan Paull
IPC分类号： B63H1100
CPC分类号： F02K7/14
摘要： The skin friction drag acting on a surface of an article travelling at high speed such as a vehicle at supersonic or particularly hypersonic speed can be reduced by introducing a fuel into the boundary layer under conditions of the fuel introduction to ensure combustion in the boundary layer. The fuel is injected through orifice(s) or a slot provided at the surface so that the fuel enters the passing fluid with a major component of the direction of injection being parallel to the local flow direction. The fuel is injected at supersonic speed, e.g. at a speed of about Mach 1.5 or higher. The invention is applicable to scramjet engines with the fuel being injected around the entire internal circumference of the wall of the scramjet engine, upstream of the commencement of the combustion chamber.
摘要翻译：通过在燃料引入的条件下将燃料引入边界层中以确保边界层中的燃烧，可以减少作用在高速行驶的物品的表面上的皮肤摩擦阻力，例如车辆如超音速或特别是超音速。燃料通过孔或设置在表面处的槽注入，使得燃料进入通过的流体，其中注射方向的主要成分平行于局部流动方向。燃料以超音速喷射，例如，速度约为1.5马赫或更高。本发明可应用于在燃烧室开始之前燃料喷射在冲击式发动机的壁的整个内圆周周围的冲击式发动机。

53. 发明授权

US5485787A Gas gun launched scramjet test projectile 失效
标题翻译：燃气枪推出了射速测试射弹
公开(公告)号：US5485787A
公开(公告)日：1996-01-23
申请号：US264207
申请日：1994-06-21
申请人： Kevin G. Bowcutt , Harry Shortland
发明人： Kevin G. Bowcutt , Harry Shortland
IPC分类号： F41A1/04 , F02K7/10 , F02K7/14 , F42B12/36 , F42B14/08 , F42B15/00
CPC分类号： F02K7/14 , F02K7/10 , F42B15/00
摘要： A gas gun-launched, propulsion-assisted scramjet projectile adapted to be fired from a gun, preferably at velocities greater than Mach 5, includes a body with an external compression section, an internal compression section, a combustion section, a nozzle section, and means for channeling ambient fluid to an engine in one of the sections of the body, the channeling means and the body cooperating with the engine to produce thrust greater than drag when the projectile travels at velocities greater than Mach 5. The projectile further includes a plurality of circumferentially spaced stabilization fins located at the nozzle region of the body and a sabot assembly releasably secured to the rear portion of the body, where the sabot assembly includes a plurality of elements joined together about the body rear portion to form a housing for protecting the body rear portion from explosive gases in the barrel of the gun.
摘要翻译：一种气枪发射的推进辅助冲击射弹，适于从枪射出，优选速度大于5马赫，包括具有外部压缩部分，内部压缩部分，燃烧部分，喷嘴部分和用于将环境流体引导到身体，引导装置和与发动机配合的主体中的一个部分中的发动机的装置，以在弹丸以大于5马赫的速度行进时产生大于阻力的推力。射弹还包括多个位于主体的喷嘴区域处的周向间隔开的稳定翼片，以及可释放地固定到主体后部的破坏组件，其中膛体组件包括围绕主体后部部分连接在一起的多个元件，以形成用于保护枪身后部爆炸性气体的身体后部。

54. 发明授权

US4170875A Caseless rocket design 失效
标题翻译：无卡火箭设计
公开(公告)号：US4170875A
公开(公告)日：1979-10-16
申请号：US694262
申请日：1976-06-10
申请人： Lawrence J. Edwards
发明人： Lawrence J. Edwards
IPC分类号： F02K7/14 , F02K9/04
CPC分类号： F02K7/14 , Y02T50/671
摘要： A "caseless" rocket having a solid propellant grain body which as a result of its shape and surface burning creates, in effect, an outer case or barrier formed by the surrounding airstream and the burning propellant. An exhaust "nozzle" is generated as an annulus in which the air stream serves as one surface while the propellant grain serves as the other. Stores or a payload are enclosed within the propellant body.
摘要翻译：由于其形状和表面燃烧，具有固体推进剂颗粒体的“无形”火箭实际上形成了由周围的气流和燃烧的推进剂形成的外壳或屏障。产生排气“喷嘴”作为其中空气流用作一个表面的环形空间，而推进剂颗粒用作另一个表面。商店或有效载荷包围在推进剂体内。

55. 发明授权

US3545212A Spindle-shaped supersonic projectile with additional propulsion by sternfiring 失效
标题翻译：通过STERNIRIR附加额外推力的主轴超级项目
公开(公告)号：US3545212A
公开(公告)日：1970-12-08
申请号：US3545212D
申请日：1967-12-14
申请人： DYNAMIT NOBEL AG
发明人： LUDWIG GUNTER
IPC分类号： F02K7/14 , F42B10/40 , F42B10/42 , F02K7/10
CPC分类号： F42B10/42 , F02K7/14 , F42B10/40

56. 发明授权

US3535882A Scramjet aircraft 失效
标题翻译： SCRAMJET飞机
公开(公告)号：US3535882A
公开(公告)日：1970-10-27
申请号：US3535882D
申请日：1966-12-27
申请人： FAIRCHILD HILLER CORP
发明人： TIZIO VINCENT JOHN , SANATOR ROBERT JOSEPH , HOLMEN ERLING GUSTAV
IPC分类号： F02K7/14 , F02K7/08 , F02K7/10
CPC分类号： F02K7/14 , Y10T137/0536

57. 发明公开

EP3098420A4 JET ENGINE, FLYING VEHICLE, AND METHOD FOR OPERATING JET ENGINE 审中-公开
标题翻译：喷气发动机飞机和运行方法喷气发动机
公开(公告)号：EP3098420A4
公开(公告)日：2017-03-22
申请号：EP15773405
申请日：2015-02-18
申请人： MITSUBISHI HEAVY IND LTD
发明人： UENO YOSHIHIKO , FURUYA SHOJIRO
IPC分类号： F02C9/28 , B64D33/02 , F02C7/228 , F02C7/232 , F02C9/44 , F02K7/14 , F02K7/18 , F23R3/28
CPC分类号： F02C9/32 , B64D33/02 , F02C7/04 , F02C7/222 , F02C7/232 , F02C9/44 , F02K7/00 , F02K7/14 , F02K7/18 , F05D2220/323 , F05D2220/80 , F05D2240/35 , F05D2250/90 , F05D2270/306 , F23N1/002 , F23N2037/02 , F23N2037/10 , F23N2041/20 , F23R3/28
摘要： A jet engine has an inlet which takes in air, a combustor (12) which combusts fuel by using the air, and a fuel control section (37) which controls supply of the fuel. The combustor (12) has a fuel supplying section (22) which supplies the fuel, injectors (20) which inject the fuel. Each injector (20) contains openings (30-1 to 30-5) which inject the fuel. The fuel supplying section (22) supplies the fuel to the injector (20) in a flow rate according to a command of an autopilot. The fuel control section (37) controls the injectors (20) such that the number of the openings (30) which inject the fuel or flow-path cross-section areas of the pipes which send the fuel in case of the low-speed is more than the number of the openings (30) which inject the fuel or the flow-path cross-section areas of the pipes which send the fuel in case of the high-speed.

58. 发明公开

EP2233727A3 Fuel-cooled flexible heat exchanger with thermoelectric device compression 有权
标题翻译：采用热电设备压缩的燃料冷却式柔性换热器
公开(公告)号：EP2233727A3
公开(公告)日：2014-03-12
申请号：EP10250566.6
申请日：2010-03-25
申请人： United Technologies Corporation
发明人： Jarmon, David C.
IPC分类号： F02K7/10 , F01D25/08 , F02K1/82 , F02K9/64 , F02K9/97 , F02K7/16 , F02K7/14 , F02C6/18 , F01D13/00 , B64D33/02 , B64C30/00 , F02C7/224 , B64D37/34 , B64D33/08
CPC分类号： F02K7/14 , B64C30/00 , B64D33/08 , B64D37/34 , B64D2033/026 , F01D13/00 , F02C6/18 , F02C7/224 , F02K1/822 , F02K7/16 , F02K9/64 , F02K9/972 , F05D2220/80 , F05D2250/15 , F05D2260/205 , F05D2260/38 , F05D2260/52 , Y02T50/44
摘要： An apparatus includes a thermoelectric (TE) device (82), a gas flow conduit (80) proximate to one side of the thermoelectric device, a plurality of flexible tubes (84) proximate to a second side of the thermoelectric device, and a spring (86) to control contact force between the flexible tubes and the thermoelectric device. The spring comprises a coil spring at least partially circumscribing the gas flow conduit. The thermoelectric device converts a temperature differential between the flexible tubes and the gas flow conduit into electrical energy.
摘要翻译：一种装置包括热电（TE）装置（82），靠近热电装置一侧的气流管道（80），靠近热电装置第二侧的多个柔性管（84），以及弹簧（86）以控制柔性管和热电装置之间的接触力。弹簧包括至少部分围绕气流管道的螺旋弹簧。热电装置将柔性管和气流管道之间的温差转换成电能。

59. 发明授权

EP0593987B1 Querschnittsgeregelter Rechteck-Lufteinlauf 失效
标题翻译：部控制的矩形空气入口
公开(公告)号：EP0593987B1
公开(公告)日：1996-04-17
申请号：EP93116240.8
申请日：1993-10-07
申请人： Daimler-Benz Aerospace Aktiengesellschaft
发明人： Weinreich, Hermann-L., Dr.
IPC分类号： B64D33/02 , F02C7/042 , F02K7/14
CPC分类号： B64D33/02 , B64D2033/026 , F02C7/042 , F02K7/14 , F05D2250/121

60. 发明公开

EP0693668A2 Gas gun launched scramjet test projectile 失效
标题翻译：从与超音速燃烧冲压操作的气体枪完成飞行测试体包括
公开(公告)号：EP0693668A2
公开(公告)日：1996-01-24
申请号：EP95109477.0
申请日：1995-06-19
申请人： ROCKWELL INTERNATIONAL CORPORATION
发明人： Bowcutt, Kevin G. , Shortland, Harry
IPC分类号： F42B15/00 , F02K7/10
CPC分类号： F02K7/14 , F02K7/10 , F42B15/00
摘要： A gas gun-launched, propulsion-assisted scramjet projectile adapted to be fired from a gun, preferably at velocities greater than Mach 5, includes a body with an external compression section, an internal compression section, a combustion section, a nozzle section, and means for channeling ambient fluid to an engine in one of the sections of the body, the channeling means and the body cooperating with the engine to produce thrust greater than drag when the projectile travels at velocities greater than Mach 5. The projectile further includes a plurality of circumferentially spaced stabilization fins located at the nozzle region of the body and a sabot assembly releasably secured to the rear portion of the body, where the sabot assembly includes a plurality of elements joined together about the body rear portion to form a housing for protecting the body rear portion from explosive gases in the barrel of the gun.
摘要翻译：一种气体枪发射，推进辅助冲压发动机抛射angepasst从枪发射，优选在比速度马赫5时，包括具有在内部压缩部分，燃烧区段，一个喷嘴部的外部压缩部的主体，和装置，用于在所述主体的所述部分中的一个引导环境流体在发动机中，窜手段和所述主体与发动机相配合以产生比拖动当弹丸在行进速度大于马赫5.射弹进一步包括多个推力更大的的周向隔开的位于所述主体的喷嘴区域和可释放地固定到所述主体，其中，所述木鞋组件包括围绕本体后部连接在一起的元件的多元化，以形成壳体，用于保护的后部的木鞋组件稳定鳍从在枪的筒体爆炸性气体本体后部。

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