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公开(公告)号：US5142862A
公开(公告)日：1992-09-01
申请号：US511891
申请日：1990-04-09
申请人： Robert B. Brown
发明人： Robert B. Brown
摘要： In the preferred configuration, the assembly is characterized in that the lateral and longitudinal thrust reversing loads exerted on the thrust reversing subassembly are transmitted into the fan duct structure which is arranged to in turn transmit these thrust reversing loads into outer structure to which the jet engine and thrust reversing assembly is mounted. In the preferred form, there are vane means which, with the thrust diverting structure in the thrust reversing position, is positioned in the thrust reversing opening to properly direct flow through the thrust reversing opening. Also in the preferred form, the thrust diverting structure is pivotally mounted to the fan duct structure at a lower location so that the thrust diverting structure rotates with a downward component of motion to the thrust reversing position, so that the thrust diverting opening is directed upwardly.
摘要翻译： 在优选的构造中，组件的特征在于，施加在推力反向组件上的横向和纵向推力反向负载被传递到风扇管道结构中，风扇管道结构被布置成将这些推力反向负载传递到外部结构中，喷气发动机 并安装推力反向组件。 在优选的形式中，存在叶片装置，其中推力转向结构处于推力反向位置，定位在推力反向开口中，以适当地引导流过推力反向开口。 同样在优选形式中，推力转向结构在较低位置枢转地安装到风扇管道结构，使得推力转向结构以向下的运动分量旋转到推力反转位置，使得推力转向开口向上指向 。
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公开(公告)号：US4069663A
公开(公告)日：1978-01-24
申请号：US700477
申请日：1976-06-28
申请人： Leslie Richard Harper , William James Lewis , David Roberts McMurtry , Lance Peter Bell , John Matthew Hall
发明人： Leslie Richard Harper , William James Lewis , David Roberts McMurtry , Lance Peter Bell , John Matthew Hall
CPC分类号： F02K1/74 , Y02T50/672
摘要： A by-pass gas turbine engine capable of producing an unmixed exhaust stream which comprises a core of hot turbine exhaust gases surrounded by an annular layer of by-pass air, is combined with a target thrust reverser. The ratio of the total pressure of the by-pass air to the total pressure of the turbine exhaust gases is arranged to be greater than unity to a significant extent, and the buckets are made from lightweight materials such as titanium, light alloys or even fiber re-inforced composite materials.
摘要翻译： 能够产生包含被环形层旁路空气包围的热涡轮机废气的核心的未混合排气流的旁通燃气轮机与目标推力反向器组合。 旁路空气的总压力与涡轮机废气的总压力的比率被设置为大于一个大的程度，并且铲斗由轻质材料制成，例如钛，轻合金或甚至纤维 重新复合材料。
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公开(公告)号：US2847823A
公开(公告)日：1958-08-19
申请号：US49438355
申请日：1955-03-15
申请人： CURTISS WRIGHT CORP
发明人： BREWER THOMAS L
CPC分类号： F02K1/74 , B64C23/005 , F02K1/60
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公开(公告)号：US11674540B2
公开(公告)日：2023-06-13
申请号：US16407438
申请日：2019-05-09
申请人： ROHR, INC.
CPC分类号： F16B17/00 , F01D25/28 , F02K1/56 , F02K1/74 , F16M13/02 , F05D2230/50 , F05D2260/30 , F05D2300/603 , F05D2300/6034 , Y02T50/60
摘要： A thrust reverser for a nacelle may comprise a composite track beam and a composite lug. The composite lug may be inserted through a through-hole in the composite track beam. Continuous fibers in the composite lug may provide strength in the in-plane direction.
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6.发明授权Pivoting door thrust reverser with controlled bypass through the rear portion of the thrust reverser door 失效枢转门推力反向器，带有控制旁路通过推力反向器门的后部
公开(公告)号：US5937636A
公开(公告)日：1999-08-17
申请号：US941633
申请日：1997-10-02
摘要： A thrust reverser is disclosed for an aircraft turbojet engine having a cowling with an inner surface forming an outer boundary of a gas flow duct, the cowling having at least one reverse thrust opening and a thrust reverser door pivotally attached to the cowling so as to move between a forward thrust position, wherein the thrust reverser door closes the at least one reverse thrust opening and a reverse thrust position, wherein a forward portion of the thrust reverser door moves outwardly from the cowing and a rear portion of the door moves inwardly into the gas flow duct so as to redirect a first portion of the gases flowing through the gas flow duct through the reverse thrust opening. The thrust reverser also includes a passageway bounded at least in part by the rear portion of the thrust reverser door located in the gas flow duct when the thrust reverser door is in the reverse thrust position, the passageway enabling a second portion of the gases flowing through the gas flow duct to pass to the rear of the thrust reverser door and to redirect this second portion of gases in an oblique direction relative to the gas flow duct to eliminate any forward thrust developed by the second portion of gases.
摘要翻译： 公开了一种用于具有整流罩的飞行器涡轮喷气发动机的推力反向器，其内表面形成气体流动管道的外边界，整流罩具有至少一个反向推力开口和枢转地附接到整流罩的推力反向器门，以便移动 在推进推力位置之间，其中推力反向器门关闭至少一个反向推力开口和反向推力位置，其中推力反向器门的前部部分从该起动器向外移动，并且该门的后部向内移动到 气流管道，以便使流经气流管道的气体的第一部分通过反向推力开口重定向。 推力反向器还包括至少部分由位于气体流动管道中的推力反向器门的后部限定的通道，当推力反向器门处于反向推力位置时，通道使第二部分气体流过 气体流动管道通过推力反向器门的后部，并且相对于气体流动管道在倾斜方向上将该第二部分气体重定向，以消除由第二部分气体产生的任何正向推力。
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公开(公告)号：US4147027A
公开(公告)日：1979-04-03
申请号：US810779
申请日：1977-06-28
CPC分类号： F02K1/60 , F02K1/74 , Y02T50/671
摘要： A thrust reverser nozzle for coaxial-flow turbofan engines comprising target-type deflector doors which are hinged for deployment about a fixed axis by means of actuation about single fixed pivots mounted on support structure on either side of the engine nacelle rearward portion. The deflector door's outer surfaces are shaped to match existing aerodynamic contours of the aircraft engine nacelle so as to provide a lower boattail angle for improved drag characteristics in the stowed or normal flight position. In that position, the deflector door interior configuration comprises a portion upstream of the engine exhaust nozzle exit plane and a downstream "fishmouth" portion through which flows hot engine exhaust gases surrounded circumferentially by cool air discharged from the engine fan. Geometry of the stowed fishmouth is sized and shaped to take advantage of mixing and shearing action between the exhaust streams so as to produce a desired variable area nozzle effect on the engine operation and thereby improve its forward thrust performance. Geometry of the upstream portion of the inside surface of the doors is sized and shaped with end plates so that when the deflector doors move to the deployed position, the exhaust streams are diverted outward and forward to produce a desired level of reverse thrust.
摘要翻译： 用于同轴涡轮风扇发动机的推力反向器喷嘴，其包括目标型偏转器门，其铰接用于通过围绕安装在发动机舱后部两侧的支撑结构上的单个固定枢轴的致动而围绕固定轴线展开。 导流门的外表面成形为匹配飞机发动机机舱的现有空气动力学轮廓，以便提供较低的飞行角度，以改善收起或正常飞行位置的阻力特性。 在该位置处，偏转器门内部构造包括发动机排气喷嘴出口平面上游的部分和下游“鱼嘴”部分，通过从发动机风扇排出的冷气将周围的热发动机排气流过。 收纳的鱼嘴的几何尺寸和形状可以利用排气流之间的混合和剪切作用，以便在发动机操作上产生期望的可变面积喷嘴效应，从而提高其前推力性能。 门的内表面的上游部分的几何尺寸和形状具有端板，使得当偏转器门移动到展开位置时，排气流向外和向前转向以产生期望的反向推力水平。
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8.发明授权Combination primary and fan air thrust reversal control systems for long duct fan jet engines 失效长风扇喷气发动机的组合主风扇和风扇空气推力反向控制系统
公开(公告)号：US4073440A
公开(公告)日：1978-02-14
申请号：US681398
申请日：1976-04-29
申请人： Donald W. Hapke
发明人： Donald W. Hapke
CPC分类号： F02K1/74 , Y02T50/671
摘要： Combination primary and fan air thrust reversal control systems for long duct fan jet engines are disclosed. In one form, the system spoils and expands primary air and, then, allows the spoiled, expanded air to exit from the fan air duct exhaust nozzle while directing fan air in a thrust reversal direction out cascade vanes circumferentially located in the aft portion of the engine nacelle. In other forms, the system directs unequal pressure fan air and primary air through separate thrust reversal ducting and out cascade vanes circumferentially located in the engine nacelle. In equal pressure fan air and primary air systems, the air may be mixed in ducting prior to being emitted from common cascade vanes, or may be maintained separate prior to emission. In still other forms, the primary air is pre-exhausted through separate nozzles located in the primary duct wall, and a portion is then exhausted through the nacelle cascade vanes. In all systems, circumferential cascade vanes are radially located in the rear portion of the engine nacelle and are exposed by rearwardly translating the aft portion of the nacelle, which forms the fan air duct exhaust nozzle. As the fan air duct exhaust nozzle is translated rearwardly, fan air duct blocker doors and, depending on the system, primary air duct blocker doors are positioned to divert the jets for thrust reversing. As an alternative to a primary air duct blocker door, the primary air duct exhaust nozzle is translated rearwardly to contact the exhaust cone or plug and, thereby, valve off the primary air duct. In this case, the fan and primary exhaust nozzles are translated rearwardly as unit.
摘要翻译： 公开了用于长风扇风扇喷气发动机的组合主风扇和风扇空气推力反向控制系统。 在一种形式中，系统破坏和膨胀一次空气，然后允许被破坏的膨胀空气从风扇空气管道排气喷嘴出口，同时将风扇空气以推力反向方向引导出来，沿着圆周方向定位在 发动机舱。 在其他形式中，系统通过单独的推力反向导管和周向位于发动机舱中的叶栅叶片引导不平等的压力风扇空气和一次空气。 在相等压力的风扇空气和一次空气系统中，空气可以在从普通级联叶片发射之前混合管道，或者可以在排放之前保持分开。 在其它形式中，主空气通过位于主管道壁中的单独喷嘴预先排出，然后一部分通过机舱叶栅叶片排出。 在所有系统中，圆周级联叶片径向地位于发动机舱的后部，并且通过向后平移形成风扇风道排气喷嘴的机舱的后部而露出。 当风扇风道排气喷嘴向后平移时，风扇风道阻塞门，并且根据系统，一次风道阻塞门被定位成转向喷流以推力反转。 作为主要风道阻塞门的替代方案，主空气管道排气喷嘴向后平移以接触排气锥体或塞子，从而隔离主空气管道。 在这种情况下，风扇和主排气喷嘴作为单元向后平移。
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公开(公告)号：US3567128A
公开(公告)日：1971-03-02
申请号：US3567128D
申请日：1969-07-02
申请人： ROHR CORP
摘要： Apparatus includes shroud positioned at rear of jet nozzle to surround and control gas stream. Shroud includes fixed portions defining lateral passages between them and pivoted doors stowed to close passages and complete shroud. When doors deploy, their trailing edges meet within shroud contour to block and deflect gas laterally. Perpendicular retractable end plates at leading edges divert gas forwardly to create reverse thrust. Back pressure from reverser tends to cause back flow into ejector barrel surrounding nozzle in area upstream of fixed portions. Retractable fences are mounted on fixed portion inner faces to intercept and redirect back flow while allowing air flow through ejector barrel in region of fixed portions. Doors are controlled to any degree of deployment for fully modulated thrust control in flight, particularly useful for tactical military aircraft.
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公开(公告)号：US3434666A
公开(公告)日：1969-03-25
申请号：US3434666D
申请日：1966-02-24
申请人： ROLLS ROYCE
发明人： SHAW WILLIAM
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