专利快速检索-快速检索全球专利，免费商用专利数据库-IPRDB

21. 发明授权

US5103634A Thrust reversing system and method 失效
标题翻译：推力换向系统及方法
公开(公告)号：US5103634A
公开(公告)日：1992-04-14
申请号：US448020
申请日：1989-12-08
申请人： Geoffrey E. Harrison , Robert B. Brown
发明人： Geoffrey E. Harrison , Robert B. Brown
IPC分类号： F02K1/56 , F02K1/72 , F02K1/74
CPC分类号： F02K1/74 , F02K1/563 , F02K1/72
摘要： An engine end and thrust reversing assembly comprising an annular thrust diverting structure which in the cruise configuration is a rearward extension of a fan duct cowl structure. For thrust reversal, the thrust diverting structure is swung rearwardly and inwardly about an inboard hinge axis to form a laterally and forwardly directed thrust reversing opening. A transversely curved blocking plate is pivotally mounted about a vertical axis to the fan duct structure, and in the cruise configuration it is positioned adjacent to a forward extension of the thrust diverting structure so as to surround a portion of the exhaust passageway. In the thrust reversing position, the blocking plate is swung to a position where it extends across the exhaust passageway defined by the thrust diverting structure.
摘要翻译：发动机端部和推力反向组件，包括环形推力转向结构，其在巡航结构中是风扇导管罩结构的向后延伸。对于推力反转，推力转向结构围绕内侧铰链轴线向后和向内摆动以形成横向和向前定向的推力反向开口。横向弯曲的阻挡板围绕垂直轴线枢转地安装到风扇管道结构，并且在巡航构造中，其被布置成与推进转向结构的向前延伸部相邻以围绕排气通道的一部分。在推力反转位置，阻挡板摆动到其延伸穿过由推力转向结构限定的排气通道的位置。

22. 发明授权

US5096144A Reverser door actuation mechanism 失效
标题翻译：逆变器门驱动机构
公开(公告)号：US5096144A
公开(公告)日：1992-03-17
申请号：US670666
申请日：1991-03-18
申请人： Ronald E. Fishwick
发明人： Ronald E. Fishwick
IPC分类号： F02K1/00 , F02K1/56
CPC分类号： F02K1/563 , F02K1/002
摘要： Reverser doors on an aircraft are to be opened, closed and splayed to effect pitch and yaw control in combination with reverse thrust. A first actuator achieves open and close control. A second actuator achieves splay control through a linkage, with the first actuator located within the linkage.
摘要翻译：飞机上的反转门将被打开，关闭并张开，以与反向推力相结合实现俯仰和偏航控制。第一个执行器实现了开启和关闭控制。第二致动器通过联动器实现喷射控制，其中第一致动器位于联动装置内。

23. 发明授权

US3986687A Aircraft propulsion system with flight maneuverable exhaust nozzle 失效
标题翻译：具有可飞行排气喷嘴的飞机推进系统
公开(公告)号：US3986687A
公开(公告)日：1976-10-19
申请号：US591879
申请日：1975-06-30
申请人： Robert G. Beavers , Kermit F. Byrd
发明人： Robert G. Beavers , Kermit F. Byrd
IPC分类号： F02K1/56 , B64D33/04 , F02K1/00 , F02K1/78 , F02K3/10 , B64C15/06
CPC分类号： B64D33/04 , F02K1/006 , Y02T50/671
摘要： An aircraft propulsion system is provided which incorporates a flight maneuverable exhaust nozzle. In one embodiment, gas turbine engines are mounted on both sides of an aircraft fuselage, each engine having an exhaust duct partially defining an exhaust stream flow path. The duct transists from a substantially cylindrical diffuser section aft of the engine to a relatively high aspect ratio section proximate the trailing edge of the wing. Exhaust gases are expelled through a thrust vectorable nozzle which is contoured within the wing and which is adapted to increase wing lift through the concept of supercirculation. Maximum aerodynamic advantage is achieved by distributing the exhaust flow over a significant portion of the wing span at the trailing edge. Thrust augmentation is provided through use of a long, flat duct burner disposed within the high aspect ratio section proximate the exhaust nozzle thereby minimizing turning losses and cooling air requirements. The exhaust nozzle includes an articulated deflector partially defining both the exhaust stream flow path and the wing upper surface. Synchronous movement of the two flaps comprising the deflector ensures proper internal area control prior to exhaust gas vectoring. The nozzle throat area is varied by a lower flap disposed in general opposition to the articulated deflector. Actuators are provided to vary the throat area and produce the proper thrust vector angle by positioning the lower flap and articulated deflector, respectively.

24. 发明授权

US3650110A Reverse thrust device for supersonic jet engine 失效
标题翻译：用于超级喷气发动机的逆向装置
公开(公告)号：US3650110A
公开(公告)日：1972-03-21
申请号：US3650110D
申请日：1970-06-02
申请人： JOHN N GHOUGASIAN
发明人： GHOUGASIAN JOHN N
IPC分类号： F02C7/26 , F02C9/16 , F02K1/56 , F02K1/20
CPC分类号： F02K1/566 , F02C7/26 , F02C9/16
摘要： Combustion products exiting from the rear turbine of a jet engine are conducted through an annular passage surrounding a rear internal body section slidably mounting an exhaust nozzle blocking piston. The exhaust nozzle is releasably locked to the engine housing in a normal mode of operation and released for displacement by the piston when extended to its nozzle blocking position for engine starting purposes and to form a reverse thrust discharge passage by rearward displacement of the nozzle.
摘要翻译：从喷气发动机的后涡轮机排出的燃烧产物通过围绕后内部主体部分的环形通道传导，该后部内部主体部分可滑动地安装排气喷嘴阻塞活塞。排气喷嘴在正常操作模式下可释放地锁定到发动机壳体，并且当延伸到其用于发动机起动目的的喷嘴阻塞位置时被活塞释放并且通过喷嘴的向后移位形成反向推力排出通道。

25. 发明授权

US3640468A Thrust reverser for asymmetric exhaust efflux deflection 失效
标题翻译：扭矩反转器用于不对称排气孔径偏差
公开(公告)号：US3640468A
公开(公告)日：1972-02-08
申请号：US3640468D
申请日：1970-03-30
申请人： LOCKHEED AIRCRAFT CORP
发明人： SEARLE NORMAN , TATOM JOHN W
IPC分类号： F02K1/56 , B64C15/06
CPC分类号： F02K1/563 , Y02T50/671
摘要： A scheme for increasing thrust reverser utilization particularly on STOL aircraft is provided whereby all of the exhaust efflux being diverted is deflected in an asymmetric direction away from the plane of the engine intake air. Exhaust ingestion is thereby reduced allowing more effective reversers to be used down to lower speeds with consequent reductions in ground roll of the aircraft. Preferably, this asymmetric deflection of the exhaust efflux is directed upwardly at an angle to the horizontal to produce an additional load on the landing gear due to the vertical component of the reverse thrust enabling greater wheelbraking force to be applied for a given wheel ground friction coefficient.
摘要翻译：提供了一种用于特别在STOL飞机上增加推力反向器利用率的方案，其中所有被转向的排气流向偏离发动机进气空气平面的非对称方向。从而减少排气，从而允许更有效的反向器被使用到较低的速度，从而降低飞机的地面滚动。优选地，排气流出的这种不对称偏转以与水平面成一定角度向上指向，以便由于反向推力的垂直分量而在起落架上产生额外的载荷，从而能够为给定的车轮地面施加更大的车轮制动力摩擦系数。

26. 发明授权

US3266734A Thrust reversers for jet propulsion engines 失效
标题翻译：喷气式推进发动机推力反向器
公开(公告)号：US3266734A
公开(公告)日：1966-08-16
申请号：US42880565
申请日：1965-01-28
申请人： ROLLS ROYCE
发明人： ROLAND GAHAGAN GEORGE , WILLIAM SHAW
IPC分类号： F02K1/56 , F02K1/60
CPC分类号： F02K1/563 , F02K1/60

27. 发明授权

US3025667A Rotary turret reversible thrust noise suppression jet engine nozzles 失效
标题翻译：旋转塔架可逆推力噪声抑制喷气发动机喷嘴
公开(公告)号：US3025667A
公开(公告)日：1962-03-20
申请号：US67325257
申请日：1957-07-22
申请人： BOEING CO
发明人： MOOREHEAD JAMES R
IPC分类号： F02K1/40 , F02K1/56
CPC分类号： F02K1/40 , F02K1/56 , Y02T50/671

28. 发明授权

US3002343A Thrust-reversing mechanism for jet aircraft 失效
标题翻译：喷气式飞机推力反转机构
公开(公告)号：US3002343A
公开(公告)日：1961-10-03
申请号：US61902256
申请日：1956-10-29
申请人： AEROJET GENERAL CO
发明人： JOHN BAIRD
IPC分类号： F02K1/56
CPC分类号： F02K1/56

29. 发明授权

US2997845A Jet propulsion nozzle adjustable to give forward and reverse thrusts 失效
标题翻译：喷气推进喷嘴可调，以提供正向和反向推力
公开(公告)号：US2997845A
公开(公告)日：1961-08-29
申请号：US72258058
申请日：1958-03-19
申请人： ROLLS ROYCE
发明人： GEORGE OULIANOFF
IPC分类号： F02K1/38 , F02K1/48 , F02K1/56
CPC分类号： F02K1/48 , F02K1/383 , F02K1/56

30. 发明授权

US2952124A Plug type noise suppressor and thrust reverser 失效
标题翻译：插头型噪声抑制器和推力反向器
公开(公告)号：US2952124A
公开(公告)日：1960-09-13
申请号：US67482757
申请日：1957-07-29
申请人： BOEING CO
发明人： PEARSON RAYMOND E
IPC分类号： F02K1/42 , F02K1/56
CPC分类号： F02K1/42 , F02K1/566

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