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1. 发明授权

US5713537A Blockerless thrust reverser 失效
标题翻译：无阻力推力反向器
公开(公告)号：US5713537A
公开(公告)日：1998-02-03
申请号：US570421
申请日：1995-12-11
申请人： Runyon H. Tindell
发明人： Runyon H. Tindell
IPC分类号： F02K1/32 , F02K1/64 , F02K1/72 , B64D33/04
CPC分类号： F02K1/72 , F02K1/32 , F02K1/64 , Y02T50/671
摘要： This specification relates to a blockerless thrust reverser for an aircraft having a podded nacelle housing a turbofan engine which produces core flow and a fan exit stream. Reverse thrust is obtained by diverting the fan exit stream into an annular slot formed in an outer wall of the nacelle where it is turned and discharged forward. The fan exit stream is directed into the annular slot by injecting high pressure streams of core flow into the fan exit stream at positions which are upstream of and adjacent to the annular slot. Reverse thrust is selectively obtained by a control means which selectively opens and closes the annular slot and the core jet injectors.
摘要翻译：本说明书涉及一种用于飞机的无阻尼推力反向器，其具有容纳涡轮风扇发动机的吊舱，其产生核心流和风扇排出流。通过将风扇出口流转向形成在机舱的外壁中的环形槽中，其被转向并向前排出，获得反向推力。通过将高压的芯流流注入到在环形槽的上游和邻近环形槽的位置处的风扇出口流中，将风扇出口流引导到环形槽中。通过选择性地打开和关闭环形槽和芯喷射喷射器的控制装置选择性地获得反向推力。

2. 发明授权

US5485975A Slotted cowl inlet lip for introducing high pressure air 失效
标题翻译：用于引入高压空气的开槽整流罩入口
公开(公告)号：US5485975A
公开(公告)日：1996-01-23
申请号：US277506
申请日：1994-07-19
申请人： Runyon H. Tindell
发明人： Runyon H. Tindell
IPC分类号： B64D29/00 , B64D29/06
CPC分类号： B64D29/00 , Y10T137/7759 , Y10T137/87812 , Y10T137/87893 , Y10T74/18808
摘要： The lower lip of an aircraft inlet cowl has a first transverse slot formed through an upper surface of the lower lip while a second transverse slot is formed through a lower surface of the lip. A rotating vane is transversely located in the interior of the lip, between the upper and lower slots. A duct located within the interior of the lower lip delivers pressurized engine bleed air to the rotating vane. Selectively driven gears position the vane so as to block either one or the other of the slots, depending upon aircraft speed, so that normal cowl inlet air is energized in the vicinity of the slot outlet. This prevents separation of the normal inlet airflow from the cowl surface - and reduces drag that would otherwise develop.
摘要翻译：飞行器入口罩的下唇具有通过下唇的上表面形成的第一横向槽，而通过唇缘的下表面形成第二横向槽。旋转叶片横向地位于唇部的内部，在上下槽之间。位于下唇内部的导管将加压的发动机排放空气传递到旋转叶片。选择性驱动的齿轮定位叶片，以便根据飞机速度阻挡一个或另一个狭槽，使得正常的整流罩入口空气在槽出口附近通电。这样可防止正常入口气流与前罩表面分离，并减少否则会发展的阻力。

3. 发明授权

US5934611A Low drag inlet design using injected duct flow 失效
标题翻译：低压入口设计使用注入管道流量
公开(公告)号：US5934611A
公开(公告)日：1999-08-10
申请号：US954553
申请日：1997-10-20
申请人： Runyon H. Tindell , Charles A. Parente
发明人： Runyon H. Tindell , Charles A. Parente
IPC分类号： B64C21/02 , B64C21/08 , B64D29/02 , B64D33/02
CPC分类号： B64C21/08 , B64C21/025 , B64C2230/06 , B64C2230/14 , B64C2230/20 , B64D2033/0226 , Y02T50/166
摘要： An air intake system disposable in an air vehicle turbo engine housing disposed in an exterior airflow for selectively reducing external engine boundary layer separation drag and external engine friction drag on the engine housing comprising an air inlet member for receiving engine intake air disposable within the engine housing. The air intake system further comprising a first air exit port disposed in fluid communication with the air inlet member, adapted to direct intake air from the air inlet member and to direct intake air substantially in the direction of exterior airflow, to reduce external engine boundary layer separation drag. The air intake system further comprising a second air exit port disposed in fluid communication with the air inlet member, adapted to direct intake air from the air inlet member and to direct intake air substantially in a direction perpendicular to the exterior airflow, to reduce external engine friction drag. The air intake system further comprising a control device for regulating intake airflow through the first and second air exit ports in response to sensed external engine conditions to mitigate at least one of external engine boundary layer separation drag and external engine friction drag.
摘要翻译：一种在空气车辆涡轮发动机壳体中可弃置的进气系统，其设置在外部气流中，用于选择性地减少发动机壳体上的外部发动机边界层分离拖曳和外部发动机摩擦阻力，包括用于接收在发动机壳体内一次性的发动机进气。进气系统还包括设置成与空气入口构件流体连通的第一空气出口，适于引导来自空气入口构件的进气并且基本上沿外部空气流的方向引导进气，以减少外部发动机边界层分离拖所述进气系统还包括设置成与所述空气入口构件流体连通的第二空气出口，适于引导来自所述空气入口构件的进气并且基本上沿垂直于所述外部气流的方向引导进气，以减少外部发动机摩擦阻力。进气系统还包括控制装置，用于响应于感测到的外部发动机状况来调节通过第一和第二空气出口的进气气流，以减轻外部发动机边界层分离拖曳和外部发动机摩擦阻力中的至少一个。

4. 发明授权

US06179251B2 Thin inlet lip design for low drag and reduced nacelle size 失效
标题翻译：薄入口唇设计，用于低阻力和减小的机舱尺寸
公开(公告)号：US06179251B2
公开(公告)日：2001-01-30
申请号：US09020081
申请日：1998-02-06
申请人： Runyon H. Tindell , Warren Davis , James J. Karanik
发明人： Runyon H. Tindell , Warren Davis , James J. Karanik
IPC分类号： B64C2104
CPC分类号： B64D33/02 , B64C21/00 , B64D29/00 , B64D2033/0226 , F02C7/04 , Y02T50/166
摘要： In accordance with the present invention, an aerodynamic turbo engine nacelle, disposable about an engine having an engine face, for mitigating boundary layer separation of intake airflow comprises an engine inlet. The engine inlet is provided with an interior surface and a curved portion. The curved portion having a leading edge. The geometry of the engine inlet is such that the ratio of the circular area defined by the diameter defined by the leading edge of the curved portion to the minimum circular area defined by the interior surface of the engine inlet is less than 1.33. The engine nacelle is further provided with a pressurized fluid injecting device for injecting pressurized fluid at the engine inlet in a direction generally parallel to intake airflow in response to sensed airflow conditions.
摘要翻译：根据本发明，用于减轻进气气流的边界层分离的，具有发动机面的发动机一次性的空气动力学涡轮发动机机舱包括发动机入口。发动机入口设有内表面和弯曲部分。弯曲部分具有前缘。发动机入口的几何形状使得由由弯曲部分的前缘限定的直径限定的圆形区域与由发动机入口的内表面限定的最小圆形区域的比率小于1.33。发动机舱还设置有加压流体喷射装置，用于响应于感测到的气流条件，在大体平行于进气气流的方向上在发动机入口处喷射加压流体。

5. 发明授权

US5904320A Blockerless thrust reverser 失效
标题翻译：无阻力推力反向器
公开(公告)号：US5904320A
公开(公告)日：1999-05-18
申请号：US900255
申请日：1997-07-25
申请人： Runyon H. Tindell
发明人： Runyon H. Tindell
IPC分类号： F02K1/32 , F02K1/64 , F02K1/72 , F02K1/74 , F02K3/02
CPC分类号： F02K1/72 , F02K1/32 , F02K1/64 , F02K1/74
摘要： A blockerless thrust reverser for an aircraft having a podded nacelle housing a turbofan engine which produces core flow and a fan exit stream. Reverse thrust is obtained by diverting the fan exit stream into an annular slot formed in an outer wall of the nacelle where it is turned and discharged forwardly. The fan exit stream is directed into the annular slot by injecting high pressure streams of core flow into the fan exit stream at positions which are upstream of and adjacent to the annular slot. Reverse thrust is selectively obtained by a control means which selectively opens and closes the annular slot and the core jet injectors.
摘要翻译：一种用于飞机的无阻力推力反向器，其具有容纳涡扇发动机的吊舱，其产生核心流和风扇排出流。通过将风扇出口流转移到形成在机舱的外壁中的环形槽中，其被转向并向前排出来获得反向推力。通过将高压的芯流流注入到在环形槽的上游和邻近环形槽的位置处的风扇出口流中，将风扇出口流引导到环形槽中。通过选择性地打开和关闭环形槽和芯喷射喷射器的控制装置选择性地获得反向推力。

6. 发明授权

US5447283A Blown boundary layer control system for a jet aircraft 失效
标题翻译：用于喷气飞机的吹制边界层控制系统
公开(公告)号：US5447283A
公开(公告)日：1995-09-05
申请号：US191252
申请日：1994-02-02
申请人： Runyon H. Tindell
发明人： Runyon H. Tindell
IPC分类号： B64C21/04 , B64D33/02
CPC分类号： B64C21/04 , B64D33/02 , B64C2230/04 , B64C2230/06 , B64D2033/026 , Y02T50/166
摘要： A blown boundary layer control system for an aircraft having a jet engine with an engine compressor, an inlet including a compression surface with an external part and internal part, a cowl lip including an internal lip surface and an external lip surface and an external afterbody. The system includes several ducts from the engine compressor. A series of nozzles and valves control and direct air flow to various surfaces. A computer is electrically connected to the valves to control the operation of the valves thereby controlling the blowing of air from a commanded number of nozzles. The computer controls the valves in position as functions of RPM of the engine, free stream flight conditions and aircraft attitude.
摘要翻译：一种用于具有具有发动机压缩机的喷气发动机的飞行器的边界层控制系统，包括具有外部部分和内部部分的压缩表面的入口，包括内唇表面和外唇表面的外罩边缘以及外部后体。该系统包括来自发动机压缩机的多个管道。一系列喷嘴和阀门控制并直接将空气流向各种表面。计算机电连接到阀门以控制阀的操作，从而控制来自指定数量的喷嘴的空气吹送。计算机将阀门作为发动机的RPM，自由流飞行条件和飞机姿态的功能控制在适当的位置。

7. 发明授权

US4979699A Flight control augmentation inlet device 失效
标题翻译：飞行控制增强进口装置
公开(公告)号：US4979699A
公开(公告)日：1990-12-25
申请号：US357182
申请日：1989-05-26
申请人： Runyon H. Tindell
发明人： Runyon H. Tindell
IPC分类号： B64C9/34 , B64C19/00 , B64D33/02
CPC分类号： B64C19/00 , B64C9/34 , B64D33/02 , B64D2033/026 , Y02T50/32 , Y10T137/0536
摘要： The invention provides a flight attitude control augmentation arrangement and method which is effective at both low speeds and at high altitudes, under conditions in which traditional flight control surfaces cannot provide sufficient air pressure differentials to develop effective control moments. The invention provides flight control surfaces at the engine air intakes of an aircraft. The flight control surfaces are flaps whose angular position determines the amount by which the intake airstream is perturbed by the flap and the consequent reaction force on the aircraft fuselage, which in turn determines the magnitude of the control moments generated by the surfaces. The net moments resulting from asymmetric deployment of the flaps are used to augment flight control moments generated by conventional flight control such as a rudder.
摘要翻译：本发明提供了在传统飞行控制表面不能提供足够的空气压力差以产生有效控制力矩的条件下在低速和高海拔地区有效的飞行姿态控制增强装置和方法。本发明在飞行器的发动机进气口处提供飞行控制表面。飞行控制表面是襟翼，其角度位置决定了进气气流被翼片扰动的量以及随之而来的对飞机机身的反作用力的影响，这反过来决定了由表面产生的控制力矩的大小。由不对称部署襟翼引起的净力矩用于增强由常规飞行控制（如方向舵）产生的飞行控制力矩。

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