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1. 发明授权

US4955565A Low drag surface 失效
标题翻译：低阻力表面
公开(公告)号：US4955565A
公开(公告)日：1990-09-11
申请号：US662983
申请日：1984-09-20
申请人： John F. Coplin
发明人： John F. Coplin
IPC分类号： B64C23/06
CPC分类号： B64C23/06 , B64C2230/04 , B64C2230/06 , B64C2230/16 , Y02T50/162 , Y02T50/166
摘要： A low drag surface comprises at its upstream edge, an intermittent linear vortex producing means which extends transverse to the flow over the surface and produces a succession of rolling vortices extending transverse to said flow. The vortices move across the surface and reduce drag in the manner of roller bearings. In preferred embodiments the vortex producing means is mechanical, in the form of an oscillating part or fluid dynamic, in the form of a nozzle arrangement.
摘要翻译：低阻力表面在其上游边缘处包括间断的线性涡流产生装置，其横向于表面上的流动延伸并且产生横向于所述流动延伸的一系列滚动涡流。涡流通过表面移动，并以滚柱轴承的方式减少阻力。在优选实施例中，涡流产生装置是以喷嘴装置形式的振动部件或流体动力学的形式的机械的。

2. 发明授权

US4484859A Rotor blade for a gas turbine engine 失效
标题翻译：用于燃气涡轮发动机的转子叶片
公开(公告)号：US4484859A
公开(公告)日：1984-11-27
申请号：US449530
申请日：1982-12-13
申请人： George Pask , John H. R. Sadler , John F. Coplin
发明人： George Pask , John H. R. Sadler , John F. Coplin
IPC分类号： F01D5/16 , F01D5/18
CPC分类号： F01D5/16 , F01D5/187 , F01D5/20 , F05D2260/201 , Y10S416/50
摘要： In order to damp possible vibration of a rotor blade for a gas turbine engine, the blade has a hollow tip portion with an internal surface extending across the direction of the centrifugal field on the blade. A weight comprising e.g. Silicon Nitride or Carbide is caused by centrifugal force to bear on this surface. Relative motion and hence friction between the weight and the surface serves to damp vibration of the blade.
摘要翻译：为了减轻用于燃气涡轮发动机的转子叶片的可能的振动，叶片具有中空的末端部分，其内表面延伸跨过叶片上的离心场的方向。重量包括氮化硅或碳化硅是由离心力引起的。重量和表面之间的相对运动和因此的摩擦力用于减轻叶片的振动。

3. 发明授权

US5182904A Gas turbine engine power unit 失效
标题翻译：气体涡轮发动机功率单元
公开(公告)号：US5182904A
公开(公告)日：1993-02-02
申请号：US791404
申请日：1991-11-14
申请人： John F. Coplin
发明人： John F. Coplin
IPC分类号： F02C3/36 , F02C7/08
CPC分类号： F02C7/08 , F02C3/36
摘要： A gas turbine engine power unit (10) comprises a gas generator (11) having a valve (21) located at its downstream end. The valve (21) receives the exhaust efflux of the gas generator (11) and directs it either to a plurality of turbochargers (32) to boost the output power of the unit (10) or to a plurality of heat exchangers (39) to provide regeneration of the unit (10). The valve (21) comprises a rotary portion (20) which rotates within a static portion (28) to provide alignment of apertures within both portions (20,28) to facilitate the direction of the gas generator (11) exhaust efflux.
摘要翻译：燃气涡轮发动机动力单元（10）包括具有位于其下游端的阀（21）的气体发生器（11）。阀（21）接收气体发生器（11）的排气流，并将其引导到多个涡轮增压器（32），以将单元（10）的输出功率或多个热交换器（39）的输出功率提升到提供单元（10）的再生。阀（21）包括旋转部分（20），旋转部分（20）在静止部分（28）内旋转以提供两个部分（20,28）内的孔的对准，以便于气体发生器（11）的排出方向。

4. 发明授权

US4793134A Fluid propulsion engine with flow exit control device 失效
标题翻译：具有流出口控制装置的流体推进发动机
公开(公告)号：US4793134A
公开(公告)日：1988-12-27
申请号：US114731
申请日：1987-10-30
申请人： John F. Coplin , Rowan H. Colley
发明人： John F. Coplin , Rowan H. Colley
IPC分类号： F02K1/78 , F02K1/08 , F02K1/68 , F02K3/04
CPC分类号： F02K1/68 , F02K1/08
摘要： A common mechanism enables both throat area change in either a fan duct or an exhaust gas duct and flow deflection at the nozzle of the duct.
摘要翻译：通常的机构使得风扇管道或废气管道中的喉部区域变化以及管道喷嘴处的流动偏转。

5. 发明授权

US4827712A Turbofan gas turbine engine 失效
标题翻译： Turbofan燃气轮机
公开(公告)号：US4827712A
公开(公告)日：1989-05-09
申请号：US123544
申请日：1987-11-20
申请人： John F. Coplin
发明人： John F. Coplin
IPC分类号： F02K3/06 , F04D29/54
CPC分类号： F04D29/545 , F02K3/06 , F05D2260/40311
摘要： A turbofan gas turbine engine comprising in axial flow series a fan, a booster compressor and a core engine is provided with a diffuser. The diffuser is positioned axially between the booster compressor and the compressor of the core engine to efficiently diffuse the air from the fan to the compressor of the core engine. The diffuser comprises a plurality of circumferentially arranged geodesic pipe diffusers, the pipe diffusers extend axially and radially and the outlets of the pipe diffusers are displaced circumferentially by an angle of between 20.degree. and 60.degree. with respect to the inlets of the pipe diffusers.The geodesic pipe diffusers allows the airflow between the fan and the core engine to be diffused adequately without compromising the efficiency of the core engine, or the high mass flow rate of the fan and also minimizes the length, weight and drag of the gas turbine engine.
摘要翻译：涡轮风扇燃气涡轮发动机具有散热器，该涡轮风扇燃气涡轮发动机具有轴流式系列，风扇，增压压缩机和核心发动机。扩散器轴向位于增压压缩机和核心发动机的压缩机之间，以有效地将空气从风扇扩散到核心发动机的压缩机。扩散器包括多个周向布置的测地管扩散器，管道扩散器沿轴向和径向延伸，并且管道扩散器的出口相对于管道扩散器的入口沿圆周方向偏移20°至60°的角度。测地管扩散器允许风扇和核心发动机之间的气流充分扩散，而不会影响核心发动机的效率，或风扇的高质量流量，并且还使燃气涡轮发动机的长度，重量和阻力最小化。

6. 发明授权

US4428713A Turbine 失效
标题翻译：涡轮
公开(公告)号：US4428713A
公开(公告)日：1984-01-31
申请号：US465457
申请日：1983-02-10
申请人： John F. Coplin , Edward S. Hadaway
发明人： John F. Coplin , Edward S. Hadaway
IPC分类号： F01D9/02 , F01D25/08 , F01D25/16 , F02C7/18 , F02C7/20 , F01D25/12
CPC分类号： F01D25/08 , F01D25/162 , Y02T50/67 , Y02T50/675
摘要： A turbine suitable for a gas turbine engine is provided with a bearing support member which is interconnected with the turbine casing by means of an annular array of aerofoil guide vanes. The whole assembly of support member and aerofoil guide vanes is maintained in a state of tension. The degree of tension in the assembly is controlled so as to be substantially constant throughout the normal operating cycle of the turbine.
摘要翻译：适用于燃气涡轮发动机的涡轮设置有轴承支撑构件，其通过翼型导叶的环形阵列与涡轮壳体互连。支撑构件和翼型导叶的整个组件保持在张紧状态。控制组件中的张力程度，使其在涡轮机的整个正常运行循环中基本恒定。

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