用于高超音速推进的反循环发动机热力性能分析

符号表fIkg空气对应的燃料流量ISP燃料比冲Ti后燃烧室出口温度马比推力，燃料空气当量比WT涡轮输出功MT飞行马赫数＄前登燃烧室出口温度。T涡轮膨胀比H飞行高度T4＊热交换器出口温度7TC压气机压比1引言八十年代以来，美、俄、德、法、英、日等主要空间大国均提出了各自的高超音速计划，如NASP、Sanger、HOTOL、STAR等。各国的方案在Ma＞6．5均采用火箭发动机或超燃冲压发动机，对于Ma＜6．5采用何种方案则分歧较大，有涡轮一冲压组合发动机方案、ATR方案、LACE方案等。本文对反循环发动机（InverseCgcleEngine）方案作了进…

THERMODYNAMIC ANALYSIS OF INVERSE CYCLE ENGINE FOR HYPERSONIC PROPULSION

Inverse Cycle Engine (ICE) is one of the candidate schemes for hypersonic air breathingpropulsion. In this paper, we use the constant specific heat method and the chemical equilib-rium thermodynamic method to analyse the specific thrust and specific impulse performancesof ICE. We also compare ICE with a ramjet engine and a turbojet with after burner. Finally,we analyses the effect of some factors on the performance of ICE, such as the temperaturelimit of the main combustor, the temperature limit of the front combustor, equivalent ratio,turbine expand ratio, etc. Based on the analysis result, we can conclude that the specificthrust performance of ICE is better than that of a ramjet engine in rich fuel mode, especiallywhen Mach number is very low (<1.5) and very high (>4.5). Some other useful results isalso obtained.