涡轮/冲压组合发动机性能分析工具

着眼于建立一套性能分析工具，可用于高超声速飞行器串联式涡轮/冲压组合动力装置总体方案的性能评估及设计约束条件分析。为了满足飞行器从起飞到飞行马赫数5宽广飞行包线内对动力装置性能的苛刻要求，所研究的组合发动机通过调整五个可调机构再加涡扇冲压燃油调节来实现变循环概念。该工具采用一维气动热力分析技术，使用了经试验验证的各部件特性，同时考虑了气体的变比热性质。通过采用面向对象的程序设计方法，该工具提供了一个性能仿真平台，可供涡扇工作模式，冲压工作模式，涡扇/冲压模式转换过程的热力循环分析，非设计点性能分析，控制规律研究等。借助于该工具，涡扇模式及冲压模式的热力循环分析结果表明，回流裕度是涡扇模式循环参数选择中需要重点考虑的因素；高的冲压燃烧室出口温度有利于提高冲压发动机的循环性能。

Performance Analysis Tool for Turbine Based Combined Cycle Engine Concept

This paper aims at developing a performance analysis tool to evaluate the performance and design constraints of a turbine based combined cycle engine concept with the tandem layout for a hypersonic cruise vehicle. To meet the conflict requirements in the long range from take-off to Mach 5, the combine cycle engine applies a variable cycle engine concept via the modulation of five variahle geometries and fuel flow. This tool uses one-dimensional aerodynamic thermodynamic analysis techniques, considering the test proved components characteristics and the property of calorically perfect gas etc. The objects oriented software design method is adopted in the tool which can affortl a plaffnrm suitable for parametric cycle analysis, performance cycle analysis and control law study of the turbofan mode, the ramjet mode and turbo/ram mode transition. Assisted by this toni, parametric cycle analysis of the turbofan mode and the ramjet mode was investigated. It shows recirculation margin is a key factor to be considered in the cycle parameters selection of the turbofan mode ; high ramjet afterburner discharge tcmperaturc is favorable to the ramjet cycle performance.