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91. 发明授权

US5224342A Latching and sealing arrangement for jet engine thrust reverser 失效
标题翻译：喷气发动机推力反向器的锁定和密封装置
公开(公告)号：US5224342A
公开(公告)日：1993-07-06
申请号：US835216
申请日：1992-02-13
申请人： Jean-Pierre Lair
发明人： Jean-Pierre Lair
IPC分类号： F02K1/60 , F02K1/76
CPC分类号： F02K1/766 , F02K1/60
摘要： A thrust reverser for jet engines comprising a pair of thrust reverser doors pivotally mounted on an axis which is substantially diametrically positioned with respect to the exhaust nozzle of a jet engine so as to pivot between a stowed position in which the doors are out of the direct path of exhaust of the engine but subjected to the static pressure of the jet engine over substantially the entire length of the doors, and a deployed position in which the doors are in the path of the engine exhaust for deflecting the exhaust and creating a braking thrust, a latch mechanism for securing the doors in the stowed position, a suitable port for directing a portion of the static pressure of the jet engine toward the doors for exerting the static pressure against the doors, an actuator for releasing the latch mechanism so that the doors may pivot to the deployed position, a valve operatively associated with the latch mechanism for relieving at least a portion of the static pressure of the jet engine acting on an upstream portion of the doors when the latch actuator is actuated, the latch actuator being incapable of releasing the latch until the static pressure is relieved from at least a portion of the doors.
摘要翻译：一种用于喷气式发动机的推力反向器，包括一对枢转地安装在轴线上的推力反向器门，所述轴线基本上相对于喷气发动机的排气喷嘴直径定位，以便在收起的位置之间枢转，发动机的排气路径，但经受大致整个门的整个长度上的喷气发动机的静压力，以及在其中门处于发动机排气路径中的展开位置，用于偏转排气并产生制动推力用于将门固定在收起位置的闩锁机构，用于将喷气发动机的静压的一部分引导向门以将静压施加于门的适当端口，用于释放闩锁机构的致动器，门可以枢转到展开位置，阀与闩锁机构可操作地相关联，用于释放喷射器的至少一部分静压力当所述闩锁致动器被致动时，所述发动机作用在所述门的上游部分上，所述闩锁致动器不能释放所述闩锁，直到所述静止压力从所述门的至少一部分释放。

92. 发明授权

US5097661A Jet engine having a planar exit opening 失效
标题翻译：喷气式发动机有平面出口打开
公开(公告)号：US5097661A
公开(公告)日：1992-03-24
申请号：US331128
申请日：1989-03-31
申请人： Jean-Pierre Lair , Etienne Fage , Thomas E. Finch
发明人： Jean-Pierre Lair , Etienne Fage , Thomas E. Finch
IPC分类号： F02K1/60
CPC分类号： F02K1/60
摘要： To eliminate the fish-mouth geometry at the downstream portion of a thrust reverser fitted jet engine which results from the formation of substantially arcuate notches when the thrust reverser doors are stowed, moveable flaps are positioned in close proximity to the doors such that when the doors are in their stowed position, the flaps would fill, at least partially, the arcuate notches to effect a substantially planar exit opening, thereby substantially eliminating the fish-mouth geometry. Moreover, the flaps can be used to effect a uniform thickness for the exit opening of the jet engine by each having a shape corresponding to that of the corresponding arcuate notch; and the principal outer surfaces and inner surfaces of the flaps provide continuity with the outer surfaces and the inner surfaces, respectively, of the doors, with the ends of the flaps have trailing edge which have thicknesses similar to those of the trailing edges of the doors. Thus, when the doors are in their stowed position, the respective trailing edges of the doors and the flaps form a minimum base surface, at the exit opening of the jet engine, in the shape of a ring having a uniform minimum thickness.
摘要翻译：为了消除在推力反向器装配的喷气发动机的下游部分处的鱼嘴几何形状，其在推力反向器门被收起时形成基本上弧形的凹口，可移动的襟翼位于门附近，使得当门处于其收起位置，翼片将至少部分地填充弧形凹口以实现基本上平面的出口，从而基本上消除鱼嘴几何形状。此外，翼片可以用于对喷气发动机的出口形成均匀的厚度，每个具有对应于相应弓形凹口的形状; 并且翼片的主要外表面和内表面分别提供与门的外表面和内表面的连续性，其中翼片的端部具有后缘，其厚度类似于门的后缘的厚度。因此，当门处于其收起位置时，门和翼片的相应后缘在喷气发动机的出口处形成具有均匀最小厚度的环形的最小基面。

93. 发明授权

US4836451A Yaw and pitch convergent-divergent thrust vectoring nozzle 失效
标题翻译：俯仰和俯仰会聚发散推力矢量喷嘴
公开(公告)号：US4836451A
公开(公告)日：1989-06-06
申请号：US095294
申请日：1987-09-10
申请人： Paul W. Herrick , Edward B. Thayer , Jim D. Stewart
发明人： Paul W. Herrick , Edward B. Thayer , Jim D. Stewart
IPC分类号： F02K1/00 , F02K1/11 , F02K1/12 , F02K1/60
CPC分类号： F02K1/11 , F02K1/008 , F02K1/1223 , F02K1/123 , F02K1/60 , F05D2250/323 , F05D2250/324 , Y02T50/671
摘要： A yaw and pitch thrust vectoring exhaust nozzle includes a spherical collar, and two surrounding clam shells hinged to a gimbal ring and pivotal about an axis perpendicular to the clam shell hinge axis. The clam shells define a variable area nozzle throat (42) which can be selectively directed vertically by rotation of the clam shells about the hinge axis (38), or horizontally by rotation of the clam shells and gimbal ring about the pivot axis (30), thereby biasing the nozzle exhaust flow vector. Divergent flaps (44, 46) further direct the exhaust downstream of the nozzle throat (42). '
摘要翻译：偏航和俯仰推力矢量排气喷嘴包括球形轴环和两个环绕的蛤壳，铰接到万向节环上并围绕垂直于蛤壳铰链轴线的轴线枢转。蛤壳限定可变区域喷嘴喉部42，其可以通过蛤壳围绕铰链轴线（38）旋转而被选择性地垂直定向，或者通过围绕枢转轴线（30）的蛤壳和万向节环的旋转水平地选择性地定向，从而偏压喷嘴排气流动矢量。发散翼片（44,46）进一步引导喷嘴喉部（42）下游的排气。

94. 发明授权

US4813607A Variable-area thrust vectoring and reversing asymmetric aircraft exhaust nozzle 失效
标题翻译：可变面积推力矢量和反转非对称飞机排气喷嘴
公开(公告)号：US4813607A
公开(公告)日：1989-03-21
申请号：US104327
申请日：1987-10-02
申请人： John E. Hill , Raymond D. Ruthven
发明人： John E. Hill , Raymond D. Ruthven
IPC分类号： F02K1/00 , F02K1/12 , F02K1/60 , B64C15/02
CPC分类号： F02K1/006 , F02K1/1223 , F02K1/60 , Y02T50/671
摘要： A variable-area, thrust vectoring, and thrust reversing aircraft propulsion nozzle includes mechanization which is uniquely simple, strong, and lightweight, as well as being able to endure the harsh, high-temperature environment of a jet engine exhaust flow. The nozzle employs a minimal number of actuators, and structure which is isolated from reversing thrust forces so that an overall objective of strength, simplicity, and lightweight is achieved by the invention.
摘要翻译：可变面积，推力矢量和推力反向飞机推进喷嘴包括机械化，其独特简单，坚固和轻便，以及能够忍受喷气发动机排气流的恶劣，高温环境。喷嘴采用最少数量的致动器，以及与反向推力隔离的结构，从而通过本发明实现了强度，简单性和轻量化的总体目标。

95. 发明授权

US4753392A Two dimensional gas turbine engine exhaust nozzle 失效
标题翻译：二维燃气轮机发动机排气喷嘴
公开(公告)号：US4753392A
公开(公告)日：1988-06-28
申请号：US667708
申请日：1984-11-02
申请人： Edward B. Thayer , George H. McLafferty
发明人： Edward B. Thayer , George H. McLafferty
IPC分类号： F02K9/86 , F02K1/12 , F02K1/60 , F02K1/62
CPC分类号： F02K1/60 , F02K1/12 , F02K1/1223
摘要： A two dimensional exhaust nozzle for a gas turbine engine having reverse thrust capability includes a pair of spaced apart converging flaps which are able to rotate about their respective axes until their downstream edges meet along the engine centerline to block the flow of gases through the engine and to redirect the flow through fixed area reverser outlet ports. The axes about which each convergent flap rotates are spaced inwardly from their respective convergent flap surfaces. The flaps themselves cover the outlet ports when the flaps are in forward thrust operating positions. The flaps move away from and unblock the outlets as they rotate to their reverse thrust position. The distance between the flap axis and its convergent surface is critical to being able to use short flaps while obtaining large reverser outlet areas.
摘要翻译：用于具有反向推力能力的燃气涡轮发动机的二维排气喷嘴包括一对间隔开的会聚翼片，其能够围绕它们各自的轴线旋转，直到它们的下游边缘沿着发动机中心线相遇，以阻挡气体通过发动机的流动，将流量重定向通过固定区域反向器出口端口。每个收敛翼片旋转的轴线与它们各自的收敛翼片表面间隔开。当襟翼处于向前推力操作位置时，襟翼本身覆盖出口。当它们旋转到其反向推力位置时，翼片离开和解除插座。襟翼轴与其收敛表面之间的距离对于能够在获得大的逆向出口区域时能够使用短襟翼是至关重要的。

96. 发明授权

US4519561A Aircraft thrust reverser mechanism 失效
标题翻译：飞机推力反向机构
公开(公告)号：US4519561A
公开(公告)日：1985-05-28
申请号：US497249
申请日：1983-05-23
申请人： Richard H. Timms
发明人： Richard H. Timms
IPC分类号： F02K1/60 , F02K1/76 , F02K1/00
CPC分类号： F02K1/605 , F02K1/763 , Y02T50/671
摘要： Thrust reverser actuation mechanisms comprising a pair of nested screwjacks commonly driven by a screwjack drive motor. The inner screwjack translates the blocker doors aft and the outer screwjack deploys the blocker doors into the engine jet stream. The screwjacks have different thread pitches so that the blocker doors are translated aft at a faster rate of speed than they are deployed into the engine jet stream.
摘要翻译：推力反向器致动机构包括通常由螺旋驱动马达驱动的一对嵌套螺丝钉。内部螺旋夹头将阻挡门向后平移，外部螺旋夹爪将阻塞门部署到发动机喷射流中。螺旋孔具有不同的螺距，使得阻挡门以比它们部署到发动机喷射流中更快的速度被翻转。

97. 发明授权

US4462207A Thrust spoiler for aero engines 失效
标题翻译：航空发动机推力扰流板
公开(公告)号：US4462207A
公开(公告)日：1984-07-31
申请号：US251339
申请日：1981-04-06
申请人： Malcolm C. Hitchcock
发明人： Malcolm C. Hitchcock
IPC分类号： F02K1/56 , F02K1/60 , F02K1/72 , F02K3/06
CPC分类号： F02K1/60 , F02K1/563
摘要： A gas turbine engine terminates at its rear in a jet pipe (14) having a fixed area nozzle (15). The engine is provided with one or more target type deflector doors (18) which in a first position constitute a rearward extension of the jet pipe (14) and define an effective exhaust nozzle (19), downstream of the nozzle (15) of the jet pipe 18, which is of smaller area than that of the jet pipe. The door, or doors 18, are movable from the first position to a second position where the nozzle 15 of the jet pipe 14 is exposed and constitutes the effective exhaust nozzle of the engine. In the second position the door, or doors 18, lie predominantly transverse to the length of the jet pipe 14 to redirect the hot gas efflux from the jet pipe 14 and reduce the forward thrust produced by the engine.
摘要翻译：燃气涡轮发动机在其后部终止于具有固定区域喷嘴（15）的喷射管（14）中。发动机设置有一个或多个目标型偏转器门（18），其在第一位置构成喷射管（14）的向后延伸并限定有效排气喷嘴（19），在喷嘴（15）的下游喷射管18的面积小于射流管的面积。门或门18可从第一位置移动到喷射管14的喷嘴15暴露的第二位置，并构成发动机的有效排气喷嘴。在第二位置，门或门18主要横向于喷射管14的长度，以重新引导来自喷射管14的热气体流出并减小由发动机产生的向前推力。

98. 发明授权

US4326682A Mounting for gas turbine powerplant 失效
标题翻译：燃气轮机动力装置的安装
公开(公告)号：US4326682A
公开(公告)日：1982-04-27
申请号：US124735
申请日：1980-02-26
申请人： Douglas J. Nightingale
发明人： Douglas J. Nightingale
IPC分类号： F02C6/20 , B64D27/26 , F02C7/20 , F02K1/60 , F02K1/74 , B64D27/20
CPC分类号： F02K1/60 , B64D27/26 , F02C7/20 , F02K1/74
摘要： A gas turbine powerplant has an inner casing (4A) containing a gas turbine engine, an outer casing (5) surrounding the inner casing, a fan driven by the engine and driving air through an annular duct defined between the casings. The powerplant is connected to an aircraft fuselage (1) by a front mounting (9,9A,9B,9C) and by a rear mounting (8,10,17,18). The front and rear mountings react lateral forces on the powerplant. The powerplant includes a thrust reverser (11) situated rearwards of the rear mounting and supported by a ring (18) lying in the annulus of the outer casing and forming part of the rear mounting. At each side of the powerplant there is provided a tie (14,15) which connects the inner casing at a joint (6,16A) adjacent the front mounting to the ring of the rear mounting. The ties therefore lie oblique to the main engine axis. The ties react the forward and reverse thrusts of the powerplant.
摘要翻译：燃气轮机动力装置具有包含燃气涡轮发动机的内壳（4A），围绕内壳的外壳（5），由发动机驱动的风扇和通过限定在壳体之间的环形导管驱动空气。动力装置通过前部安装（9,9A，9B，9C）和后部安装（8,10,17,18）连接到飞机机身（1）。前后安装对动力装置施加横向力。动力装置包括位于后部安装件后方并由位于外壳的环形空间中并形成后部安装件的一部分的环（18）支撑的推力反向器（11）。在动力装置的每一侧设置有一个连接件（14,15），该连接件将内部壳体连接在与前部安装件相邻的后部安装件的环上的接头（6,16A）处。因此，系带倾斜于主发动机轴线。领带反应了动力装置的正向和反向推力。

99. 发明授权

US4212442A Thrust reverser 失效
标题翻译：推力倒车
公开(公告)号：US4212442A
公开(公告)日：1980-07-15
申请号：US881045
申请日：1978-02-24
申请人： Etienne Fage
发明人： Etienne Fage
IPC分类号： F02K1/60 , F02K1/76 , B64D33/04
CPC分类号： F02K1/76 , F02K1/60 , F02K1/766
摘要： The invention relates to a thrust reverser for a jet engine of an aircraft, which comprises two symmetrical doors pivotally mounted about an axis which is transverse and substantially diametrical to the jet of said engine and which is disposed downstream of the jet exhaust pipe thereof, the doors each being pivoted due to two diametrically opposite hinges and occupying a folded or stowed position in which they form part of the fairing of the engine or fuselage of the aircraft, or an unfolded or opened out position in which they are disposed transversely to the jet, while at least one longitudinal jack is provided at the level of a hinge, for the simultaneous control of the doors via connecting rods. According to the invention, this reverser is characterized, on the one hand, in that the jack comprises two aligned pistons rigidly connected by a common intermediate piston rod, each piston being housed in a corresponding cylinder and the two cylinders being rigidly connected together, and, on the other hand, in that the connecting rods for controlling the doors are pivoted on the intermediate piston rod. The invention finds particular application to the braking of aircraft.
摘要翻译：本发明涉及一种用于飞行器的喷气发动机的推力反向器，其包括两个对称的门，所述两个对称的门围绕一个轴线枢转地安装，所述轴线基本上与所述发动机的射流横向并且基本上直径相对，并且设置在其喷射排气管的下游每个门由于两个直径相对的铰链枢转并且占据折叠或收起的位置，在这些位置中它们形成飞行器的发动机或机身的整流罩的一部分，或者展开或打开的位置，其中它们横向于喷嘴而在铰链的水平处设置至少一个纵向千斤顶，用于通过连接杆同时控制门。根据本发明，这种反向器的特征在于，一方面，千斤顶包括通过公共中间活塞杆刚性连接的两个对准的活塞，每个活塞容纳在相应的气缸中，并且两个气缸刚性连接在一起，以及另一方面，用于控制门的连杆在中间活塞杆上枢转。本发明特别适用于飞机的制动。

100. 发明授权

US4182501A Thrust reverser for jet engine forming active extension of jet tube 失效
标题翻译：用于喷气发动机的推力反向器形成喷射管的主动延伸
公开(公告)号：US4182501A
公开(公告)日：1980-01-08
申请号：US881044
申请日：1978-02-24
申请人： Etienne Fage
发明人： Etienne Fage
IPC分类号： B64C25/42 , B64D33/04 , F02K1/60 , B64C15/06
CPC分类号： B64D33/04 , B64C25/423 , F02K1/60 , Y02T50/671
摘要： The invention relates to a thrust reverser comprising two symmetrical doors, approximately hemi-truncated in shape, pivotally mounted about an axis which is transverse and substantially diametrical to the jet of a jet engine and which is disposed downstream of the jet exhaust pipe thereof, the doors occupying a folded, or stowed, position in which they determine a sleeve forming part of the fairing of the engine and fuselage of the aircraft, or an unfolded, or opened out, position in which they are disposed transversely with respect to the jet, wherein the structure of each of the doors is such that, in stowed position, the inner volume of the sleeve forms a useful extension of the jet pipe of the engine. The invention finds particular application in the braking of aircraft.
摘要翻译：本发明涉及一种推力反向器，其包括两个对称的门，大致半截形形状，围绕与喷气发动机的射流横向且基本上直径的轴枢转地安装，并且位于其喷射排气管的下游，门占据折叠或收起的位置，在这些位置中，它们确定形成发动机的整流罩和飞行器的机身的一部分的套筒，或者它们相对于射流横向设置的展开或打开的位置，其中每个门的结构使得在收起位置中，套筒的内部容积形成发动机的喷射管的有用延伸部。本发明特别适用于飞机制动。

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