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1. 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。

2. 发明授权

US5167117A Method and apparatus for cooling an airplane engine 失效
标题翻译：用于冷却飞机发动机的方法和装置
公开(公告)号：US5167117A
公开(公告)日：1992-12-01
申请号：US631157
申请日：1990-12-20
申请人： Claus Herzog , Rainer R. Schwab , Klaus Rud , Harald Mark
发明人： Claus Herzog , Rainer R. Schwab , Klaus Rud , Harald Mark
IPC分类号： B64D33/02 , F02C7/16 , F02K7/18
CPC分类号： B64D33/02 , F02C7/16 , F02K7/18 , B64D2033/026 , Y02T50/671 , Y02T50/675
摘要： An apparatus for cooling components of an airplane engine at least partially operated by a cryogenically stored propellant via cooling air includes an air supply line for supplying the cooling air from an outside environment. A heat exchanger exchanges the cooling air with the propellant to precool the cooling air and includes a condenser having an in-flow and an out-flow side connected to the air supply line for precooling the cooling air. A pump is coupled to a cooling air line for conveying the precooled air in a liquid or vapor state to the components to be cooled wherein the cryogenically stored propellant acts upon the condenser. A propellant tank is connected to the in-flow side of the condenser and stores the cryogenically stored propellant, wherein the out-flow side of the condenser is connected to at least one combustion system of the airplane engine.
摘要翻译：至少部分由经低温储存的推进剂通过冷却空气操作的用于冷却飞机发动机部件的装置包括用于从外部环境供应冷却空气的空气供应管线。热交换器将冷却空气与推进剂交换以预冷却冷却空气，并且包括冷凝器，其具有连接到空气供应管线的流入侧和外流侧，用于预冷却冷却空气。泵耦合到冷却空气管线，用于将液体或蒸气状态的预冷空气输送到要冷却的部件，其中低温储存的推进剂作用在冷凝器上。推进剂罐连接到冷凝器的流入侧，并存储低温存储的推进剂，其中冷凝器的外流侧连接到飞机发动机的至少一个燃烧系统。

3. 发明授权

US4999994A Turbo engine 失效
标题翻译：涡轮发动机
公开(公告)号：US4999994A
公开(公告)日：1991-03-19
申请号：US398445
申请日：1989-08-25
申请人： Klaus Rud , Alois Rohra
发明人： Klaus Rud , Alois Rohra
IPC分类号： F02C7/06 , F02C7/047 , F02C7/14 , F02C7/32
CPC分类号： F02C7/14 , F02C7/047 , Y02T50/671 , Y02T50/675
摘要： A turbo engine with a gas turbine to drive propellers or propfan blades is disclosed which includes a speed reduction transmission interposed behind the gas turbine output drive shaft and the propellers or propfan blades. A cooling air impeller is provided to provide the supply of cooling air to an oil cooler for the speed reduction transmission. The impeller is arranged directly on the turbine output drive shaft.
摘要翻译：公开了一种具有用于驱动螺旋桨或螺旋叶片的燃气轮机的涡轮发动机，其包括介于燃气轮机输出驱动轴和螺旋桨或螺旋叶片之后的减速传动装置。设置冷却空气叶轮以提供冷却空气供给用于减速传动的油冷却器。叶轮直接布置在涡轮输出驱动轴上。

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