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HYPERSONIC RAMJET ENGINE WITH BALANCED VARIABLE MECHANISMS

机译：具有平衡变量机制的超音速拉姆机

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摘要

The variable air intake and variable exhaust nozzles of hypersonic engines are designed and tested in this study. Dimensions for variable geometry air intake, ram combustor, and variable geometry exhaust nozzle are defined based on the requirements of a precooled turbojet engine. A hypersonic ramjet engine is designed as a scaled test bed for each component. Actuation forces of moving parts for variable intake and variable nozzle are reduced by balancing the other forces in the opposite direction. A demonstrator engine that includes variable intake and variable nozzle is designed and the components are fabricated. Composite material with silicone carbide is applied for high-temperature walls of ram combustor. Internal cooling structure is adopted for both moving and static parts of the variable nozzle. Pressure recovery and mass capture ratio of the variable intake at Mach 5 is obtained by a hypersonic wind tunnel test. Flow characteristics of the variable nozzle are obtained by a low-temperature flow test. Wall temperature and heat flux of the nozzle at Mach 3 is obtained by a firing test. Consequently, the intake and the nozzle are proved to be used at the designed pressure and temperature environment.
机译：本研究设计和测试了超音速发动机的可变进气口和可变排气嘴。根据预冷涡轮喷气发动机的要求，定义了可变几何形状的进气口，冲压燃烧室和可变几何形状的排气喷嘴的尺寸。高超音速冲压发动机被设计为每个组件的缩放测试台。通过平衡相反方向上的其他力，可减小用于可变进气和可变喷嘴的运动部件的致动力。设计了包括可变进气量和可变喷嘴的演示发动机，并制造了零部件。带有碳化硅的复合材料被应用于冲压燃烧室的高温壁。可变喷嘴的活动和静止部分均采用内部冷却结构。通过高超音速风洞试验获得了马赫数为5时可变进气口的压力恢复和质量捕获率。可变喷嘴的流动特性通过低温流动试验获得。通过燃烧试验获得在3马赫的喷嘴的壁温和热通量。因此，事实证明，进气口和喷嘴可在设计的压力和温度环境下使用。

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