高超声速串联式组合动力装置方案

为保证高超声速运输机在宽广的飞行包线内(Ma＝0~5,H=0~30km)稳 定可靠工作,对涡轮/冲压组合动力装置串联方案展开研究.首先建立了经试验数据校核的 适于高超声速飞行的组合动力装置部件级变循环详细非线性性能计算模型;在此基础上,利 用发动机设计点热力循环分析和非设计点性能分析方法对串联方案的综合特性进行评估,最 终给出一种经过优化的串联布局涡扇/冲压组合动力装置总体性能设计方案.研究结果表明 ,优化方案可有效地缩小组合发动机的结构尺寸与重量,有利于进气道,喷管的调节以及冲 压燃烧室燃烧的组织.通过综合调整发动机5个可调几何部位以及涡轮发动机燃油流量和冲 压燃烧室燃油流量,可以实现涡扇/冲压模式的平稳转换. 

Hypersonic combined cycle engine concept with tandem layout

Hypersonic turbo/ramjet combined cycle engine concept with the t andem layout was investigated to ensure that the civic aircraft can work reliabl y under a wide range of flight envelope(Ma＝0~5,H=0~30km).A non-linear combin e cycle engine model controlled by multiple variables was developed and verified . Based on it, an optimized scheme was then worked out after comprehensive evalu ation on the propulsion system integration via the parametric cycle analysis and performance cycle analysis. This scheme is favorable to the reduction in system dimension and weight, the adjustment of the shared inlet and exhaust nozzle, as well as the stability of the ram combustion. Transient simulation on the turbo/ ram mode transition was also conducted. Results show that stable mode transition could be acquired through proper modulation of five variable geometries and the fuel flow.