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1. 发明授权

US5645127A Coolant supply arrangement for jet engine turbine walls 失效
标题翻译：喷气发动机涡轮机壁的冷却液供应装置
公开(公告)号：US5645127A
公开(公告)日：1997-07-08
申请号：US240585
申请日：1994-05-09
申请人： Heinrich Enderle , Achim Ottenstein
发明人： Heinrich Enderle , Achim Ottenstein
IPC分类号： F02C7/16 , F02K1/82 , F02K7/16 , F02K7/18 , F02K9/64 , F02K9/78 , F02K9/97 , F23R3/00 , F28F3/12 , F28F9/02 , F28F9/18 , F28D7/06
CPC分类号： F02K1/822 , F02K9/972 , F23R3/002 , F28F3/12 , F28F9/0243 , F28F9/18 , F28F2009/0297
摘要： An arrangement is disclosed for distributing and supplying and removing a coolant to and from a wall of a turbine engine, in particular a turbine dynamic jet engine, which is subjected to the flow of a hot fluid and has cooling channels which can be acted upon by the coolant and which are arranged substantially parallel to one another in the wall. The arrangement includes tube guides which are spatially separated from one another and connected to the wall, a casing of each tube guide having a longitudinal slot, each tube guide being attached on an inlet or outlet side to the respective cooling channels by way of the longitudinal slot and apertures in the wall, and a soldering or welded seam connecting the tube guides to the wall along the respective longitudinal slot.
摘要翻译：公开了用于将涡轮发动机，特别是涡轮机动力喷气发动机的壁分配和供给和从其中移出冷却剂的布置，涡轮机动力喷气发动机经受热流体的流动，并且具有能够被冷却剂并且其在壁中彼此基本平行地布置。该装置包括在空间上彼此分离并连接到壁的管引导件，每个管引导件的壳体具有纵向狭槽，每个管引导件通过纵向方向附接到相应的冷却通道的入口侧或出口侧壁上的槽和孔，以及沿着相应的纵向槽将管引导件连接到壁的焊接或焊缝。

2. 发明授权

US5148673A Integrated turboramjet engine 失效
标题翻译：集成涡轮发动机
公开(公告)号：US5148673A
公开(公告)日：1992-09-22
申请号：US602761
申请日：1990-10-24
申请人： Heinrich Enderle
发明人： Heinrich Enderle
IPC分类号： F02C7/00 , F02C7/042 , F02K7/16
CPC分类号： F02K7/16 , F02C7/042 , Y10T137/0536
摘要： An integrated turboramjet engine has an axially slidable inlet cone, a rigid guide ring arranged concentrically outside the inlet cone, and a lock ring which can be slid axially against the inlet cone, whereby the air volume flowing into the air inlet can be introduced alternately into a turbo-inlet duct or a ram-air inlet duct in a low-loss and flow-promoting manner.
摘要翻译：集成的涡轮喷气发动机具有可轴向滑动的入口锥体，同心地设置在入口锥体外部的刚性导向环和可以相对于入口锥体轴向滑动的锁定环，由此可以将流入空气入口的空气体积交替地引入以低损耗和流动促进方式的涡轮进口管道或冲压空气入口管道。

3. 发明授权

US5094070A Propelling nozzle for a hypersonic jet plane 失效
标题翻译：喷气喷嘴用于高性能喷气飞机
公开(公告)号：US5094070A
公开(公告)日：1992-03-10
申请号：US505044
申请日：1990-04-05
申请人： Heinrich Enderle
发明人： Heinrich Enderle
IPC分类号： B64D27/02 , F02K1/12 , F02K1/60 , F02K1/62 , F02K7/16
CPC分类号： F02K7/16 , F02K1/1215 , F02K1/1223 , F02K1/60
摘要： A propelling nozzle for a hypersonic jet plane having movable upper and lower primary and secondary flaps assigned to the gas turbojet engine as well as to the ramjet engine, both engines being arranged axially above one another, their outlet ducts being separated by means of a partition extending in the downstream direction to the narrowest cross-section of the propelling nozzle. The nozzle flaps can place themselves against the end edge of the partition on both sides in a manner advantageous with respect to the flow in the transition area from the primary flaps to the secondary flaps. As a result, each of the two outlet ducts can advantageously, either alternatively or simultaneously, be closed or opened, while, at the same time, a narrow cross-section and a divergence of the propelling nozzle can be adjusted which are optimal for the respective flying Mach number.
摘要翻译：用于超音速喷射平面的推进喷嘴，其具有分配给气体涡轮喷气发动机以及冲压喷气发动机的可移动的上部和下部主要和次级翼片，两个发动机彼此轴向地布置，它们的出口管道通过分隔件沿下游方向延伸到推进喷嘴的最窄横截面。喷嘴襟翼可以以相对于从主襟翼到次襟翼的过渡区域中的流动有利的方式将自身置于两侧的隔板的端边缘上。结果，两个出口管道中的每一个可以有选择性地或同时地被闭合或打开，同时，可以调节窄的横截面和推进喷嘴的发散，这对于各自飞行马赫数。

4. 发明授权

US5165228A Turboramjet engine 失效
标题翻译：涡轮发动机
公开(公告)号：US5165228A
公开(公告)日：1992-11-24
申请号：US654195
申请日：1991-02-12
申请人： Heinrich Enderle
发明人： Heinrich Enderle
IPC分类号： F02C7/042 , F02K7/16
CPC分类号： F02C7/042 , Y02T50/671 , Y10T137/0536
摘要： Turboramjet engine having a variable air intake, a ram air duct annularly enveloping the basic turbojet engine, and shutoff devices with which the ram air duct is energized with air when the basic turbojet engine is shut off and with which the basic turbojet engine is energized with air when the ram air duct is shut off. An air tract communicates with the air intake on a tubular duct carried axially on the basic turbojet engine and expands to an annular inlet section to the ram air duct. The shutoff devices are associated at least on the inlet side with quadrilateral sections of the tubular duct. As shutoff means for the inlet flow, use is made of an axially adjustable and internally swept sleeve valve and at least one flap that can be pivoted against a partial inlet area of the inlet section, which flap seals off the sleeve valve in lid-fashion when the inlet section is in a jointly exposed position.
摘要翻译：具有可变进气口的涡轮喷气发动机，环形地包围基本涡轮喷气发动机的冲压空气管道和当基本涡轮喷气发动机关闭并且基本涡轮喷气发动机通过其与空气通过时，冲压空气管道被通电的关闭装置当冲压风道关闭时，空气流通。空气管道与在基本涡轮喷气发动机上轴向承载的管状管道上的进气口连通，并且膨胀到到冲压空气管道的环形入口部分。关闭装置至少在入口侧与管状管道的四边形部分相关联。作为入口流动的关闭装置，使用可轴向调节和内部扫过的套筒阀以及至少一个挡板，其能够抵靠入口部分的部分入口区域枢转，该挡板以盖子方式密封套筒阀当入口部分处于共同暴露的位置时。

5. 发明授权

US5054285A Thrust reverser for turbofan engine 失效
标题翻译： TURBOFAN发动机扭矩反转器
公开(公告)号：US5054285A
公开(公告)日：1991-10-08
申请号：US451141
申请日：1989-12-15
申请人： Helmjut-Arnd Geidel , Heinrich Enderle , Alois Rohra
发明人： Helmjut-Arnd Geidel , Heinrich Enderle , Alois Rohra
IPC分类号： F02K1/70 , F02K1/72
CPC分类号： F02K1/72
摘要： A gas turbine jet engine is disclosed with a fan delivering into a bypass duct to generate mainly propulsion thrust, and with a thrust reversing device having flaps which for reverse thrust operation pivot into the fan air stream and cooperate with an axially extended extreme section of the outer wall of the bypass duct to uncover delection ports arranged at breakthroughs in the outer wall. The extreme section of the outer wall and the thrust reverser flaps are linked one with the other for relative movement between them such that in a first phase of actuation relative to a fixed extreme nozzle section, the extreme section provides an additional fan nozzle area which communicates with the inlet flow areas formed by the flaps relative to the bypass duct.
摘要翻译：公开了一种燃气轮机喷气发动机，其具有输送到旁路管道中的风扇，以主要产生推进推力，并且具有用于反向推力操作的折翼的推力反向装置枢转到风扇空气流中并与轴向延伸的旁路管道的外壁以露出设置在外壁上的突破处的选择端口。外壁和推力反向器襟翼的极限部分与另一个相互连接以在它们之间进行相对运动，使得在相对于固定的极限喷嘴部分的致动的第一阶段中，极端部分提供了一个附加的风扇喷嘴区域，其连通其中由翼片相对于旁路管道形成的入口流动区域。

6. 发明授权

US5186390A Propelling nozzle 失效
标题翻译：螺旋喷嘴
公开(公告)号：US5186390A
公开(公告)日：1993-02-16
申请号：US721641
申请日：1991-09-19
申请人： Heinrich Enderle , Jorg Heyse , Helmut-Arnd Geidel
发明人： Heinrich Enderle , Jorg Heyse , Helmut-Arnd Geidel
IPC分类号： F02K1/12
CPC分类号： F02K1/1223 , F02K1/1215 , F02K1/1269
摘要： A propelling nozzle has upper and lower primary and secondary flaps which are disposed opposite one another at a mutual distance and which are sealingly movably guided between lateral wall portions of a four-cornered nozzle housing. The primary flaps are arranged pivotally about a fixed axis of rotation on the nozzle housing. The secondary flaps, in each case upstream of levers non-rotatably connected with the primary flaps, are pivotally linked to pivots situated on the side facing away from the nozzle flow. The secondary flaps change into the primary flaps with a surface section which is bent concentrically with respect to the pivots. The primary and secondary flaps are arranged in a four-cornered nozzle housing which is itself closed in. In each case the secondary flaps are arranged on the nozzle housing in an axially movable and angularly adjustable manner at the downstream end. The levers are formed on interior sections which are bent away from the primary flaps in a toggle-lever-type manner. At the rearward ends of the levers, pivots are located. The levers have cutouts which are concentric with respect to the pivots. The surface sections of the secondary flaps can be moved into the cutouts. The upper and the lower primary and secondary flaps can be swivelled by means of their respective separate adjusting system. Each adjusting system is arranged between an upper or a lower wall portion of the nozzle housing and the flaps and, in the process, acts upon a primary or a secondary flap.
摘要翻译： PCT No.PCT / DE90 / 00020 Sec。 371日期1991年9月19日 102（e）1991年9月19日PCT PCT 1990年1月16日PCT公布。出版物WO90 / 08254 日期：1990年7月26日。推进喷嘴具有彼此相对设置的彼此相对设置并且在四角喷嘴壳体的侧壁部分之间被密封地可移动地引导的上部和下部主要和次要折翼。主翼片围绕喷嘴壳体上的固定旋转轴线枢转布置。次级翼片（在每种情况下都不与主翼片不可旋转地连接的杆的上游）枢转地连接到位于远离喷嘴流动的一侧的枢轴。次级翼片变成主翼片，其中相对于枢轴同心弯曲的表面部分。主瓣和副翼被布置在四角喷嘴壳体中，其四周封闭。在每种情况下，次级翼片在下游端以可轴向移动和角度可调节的方式布置在喷嘴壳体上。杠杆形成在以肘杆式方式从主瓣折回的内部部分上。在杠杆的后端，枢轴位于。杆具有相对于枢轴同心的切口。次级襟翼的表面部分可以移动到切口中。上，下主瓣可以通过各自的单独的调节系统进行旋转。每个调节系统布置在喷嘴壳体的上壁部分或下壁部分与翼片之间，并且在该过程中，其作用在主瓣或副皮瓣上。

7. 发明授权

US5170964A Propelling nozzle for the thrust vector control for aircraft equipped with jet engines 失效
标题翻译：用于喷气发动机的飞机的扭矩矢量控制的推进喷嘴
公开(公告)号：US5170964A
公开(公告)日：1992-12-15
申请号：US768573
申请日：1991-11-01
申请人： Heinrich Enderle , Klaus Rud , Helmut-Arnd Geidel
发明人： Heinrich Enderle , Klaus Rud , Helmut-Arnd Geidel
IPC分类号： B64C15/02
CPC分类号： B64C15/02
摘要： The proposal is for a thrust nozzle for aircraft fitted with jet engines especially for lateral thrust vector control, in which the upstream ends of at least two flaps (8, 12) actuated via lever-like adjusters are arranged to pivot simultaneously at different angles of rotation about spindles running across the nozzle axis (20) and between walls (22, 23) running substantially parallel to the nozzle axis of a square nozzle housing in such a way that, with a permanently convergent nozzle contour, a narrowest cross-section is formed between the flaps (8, 12) at the outlet side; one end of each lever-like adjuster (28, 29) is to engage in downstream ends of the flaps, said adjusters being arranged at their movably mutually coupled other ends to travel in a guide path (30) which is curved so as to produce continuously different flap rotation angles; one or more narrowest cross-sections can either be kept continuously constant or change dependently upon the jet deflection angle.
摘要翻译： PCT No.PCT / DE90 / 00226 Sec。 371日期1991年11月1日 102（e）1991年11月1日PCT PCT 1990年3月21日PCT公布。出版物WO90 / 11222 日期为1990年10月4日。该建议是针对装有喷气发动机的飞机的推力喷嘴，特别是用于横向推力矢量控制，其中布置经由杠杆状调节器致动的至少两个翼片（8,12）的上游端以围绕穿过喷嘴轴线（20）的主轴和基本上平行于方形喷嘴壳体的喷嘴轴线延伸的壁（22,23）之间的不同旋转角度同时枢转，使得具有永久收敛的喷嘴轮廓在出口侧的翼片（8,12）之间形成最窄的横截面; 每个杠杆状调节器（28,29）的一端将接合在翼片的下游端，所述调节器布置在其可移动的相互耦合的另一端处，以在导轨（30）中行进，所述引导路径（30）弯曲以产生连续不同的皮瓣旋转角度; 一个或多个最窄的横截面可以保持连续恒定或者依赖于喷射偏转角来改变。

8. 发明授权

US5058378A Integrated turboramjet engine 失效
标题翻译：集成涡轮发动机
公开(公告)号：US5058378A
公开(公告)日：1991-10-22
申请号：US505043
申请日：1990-04-05
申请人： Heinrich Enderle
发明人： Heinrich Enderle
IPC分类号： F02C7/042 , F02K3/075 , F02K7/16
CPC分类号： F02K3/075 , F02C7/042 , F02K7/16
摘要： A change-over arrangement for an integrated turboramjet engine has a guide ring which can be displaced in the axial direction and an annular cone which can be displaced against the guide ring. In the turbo-operation, the annular cone is in its front position and the guide ring is in its rear position closing off a ram air inlet duct, and in the ramjet operation, the annular cone, in its rear position, closes off the turbo-inlet duct, and the guide ring opens up the ram air inlet duct. As a result, a low-loss introduction of the air current can take place into the turbo-inlet duct or into the ram air inlet duct, without, at the same time, requiring disadvantageous enlargements of the diameter of the outer casing of the engine.
摘要翻译：用于集成的涡轮喷气发动机的转换装置具有可沿轴向移位的导向环和能够抵靠引导环移位的环形锥体。在涡轮操作中，环形锥体处于其前部位置，并且导向环处于其后部位置，关闭冲压空气入口管道，并且在冲压喷射操作中，环形锥体在其后部位置处封闭涡轮 - 导管，导向环打开冲压进气管。结果，可以在涡轮进口管道或冲压空气入口管道中进行低损耗的气流引入，而不需要同时增大发动机外壳的直径。。

9. 发明授权

US3989192A Device for varying the gas exit area of an exhaust nozzle for a jet deflecting device 失效
标题翻译：用于改变用于喷射偏转装置的排气喷嘴的气体出口区域的装置
公开(公告)号：US3989192A
公开(公告)日：1976-11-02
申请号：US553884
申请日：1975-02-28
申请人： Heinrich Enderle , Alfred Jabs
发明人： Heinrich Enderle , Alfred Jabs
IPC分类号： F02K1/00 , F02K1/12 , B64C15/08
CPC分类号： F02K1/1207 , F02K1/004 , Y02T50/671
摘要： A jet deflecting device has a first rotatable pipe section connected to thend of an engine jet pipe and a second pipe section rotatably connected to the end of the first pipe section. Nozzle flaps are provided at the end of the second pipe section, and coupled to be moved inwardly and outwardly in response to axial movement of a nozzle actuating skirt slidably mounted at the end of the second pipe section. A first drive motor on the stationary jet pipe directly rotates the first pipe section by way of driving gears. A second drive motor is coupled by gears to rotate the second pipe section independently of rotation of the first pipe section, and a third drive motor is provided for rotating an angular gear carrier on the second pipe section independently of the angular position of the two pipe sections. An angle drive mechanism is provided for converting rotational movement of the angular gear carrier to axial movement of the nozzle actuating skirt for control of the nozzle flaps. A common planetary gear arrangement may be provided for the second and third drive motors.
摘要翻译：喷射偏转装置具有连接到发动机喷射管的端部的第一可旋转管段和可旋转地连接到第一管段的端部的第二管段。喷嘴襟翼设置在第二管段的端部处，并且响应于可滑动地安装在第二管部分的端部处的喷嘴致动裙部的轴向移动而联接成向内和向外移动。固定喷射管上的第一驱动马达通过驱动齿轮直接旋转第一管段。第二驱动马达通过齿轮联接以独立于第一管段的旋转而旋转第二管段，并且提供第三驱动马达用于在第二管段上独立于两个管的角位置旋转角齿轮架部分。提供一种角度驱动机构，用于将角齿轮架的旋转运动转换成喷嘴致动裙的轴向运动，以控制喷嘴翼。可以为第二和第三驱动马达提供常见的行星齿轮装置。

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