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基于两级入轨高超声速飞行器方案,确定了涡轮基组合循环发动机设计点各参数,设计了飞行器进排气系统,编写了推进系统安装损失计算程序,采用数值模拟技术研究了沿飞行轨迹的涡轮基组合循环发动机/飞行器一体化性能,计算结果显示,跨声速阶段的安装损失最大,溢流阻力在跨声速区域具有主要的影响,在工作模式转换结束后,安装损失会有一定的增长,这是因为喷管喉部气流总压降低,致使流经发动机的气流流量减少,造成溢流阻力和旁路放气阻力的增加所致。
Based on the two-stage orbit hypersonic vehicle program, the design parameters of the turbine-based combined cycle engine are determined, the air intake and exhaust system of the aircraft is designed, the calculation program of the propulsion system installation loss is compiled, and the numerical simulation technology is used to study the performance of the turbine Based on the integrated performance of the combined cycle engine and the aircraft, the calculation results show that the installation loss is the largest during the transonic stage, and the overflow resistance has a major impact on the transonic region. After the conversion of the working mode, the installation loss will increase to a certain extent, The reason is that the total pressure of the throat of the nozzle decreases and the flow of the air flowing through the engine decreases, resulting in the increase of the overflow resistance and the bypass deflation resistance.