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在常规大涵道比涡扇发动机热力循环基础上增加间冷过程和回热过程,发展了间冷回热循环航空发动机(IRA)的计算模型和相应的性能仿真程序.分析了采用间冷回热技术的分排大涵道比涡扇发动机的热力循环参数选择与匹配.结果表明:间冷度、回热度、外涵道间冷用气量、增压级和高压压气机压比分配、总增压比、涵道比等热力循环参数对IRA的性能有很大影响;合理应用间冷回热技术,并优化发动机热力循环参数匹配可以显著改善发动机的性能.
Based on the conventional large bypass ratio turbofan thermodynamic cycle, intercooling process and reheating process were added, and the calculation model and corresponding performance simulation program of intercooled heat cycle aero-engine (IRA) were developed. The results show that the intercooling degree, the degree of recuperation, the amount of cold gas between external ducts, the pressure ratio of supercharger and high pressure compressor, the total Turbocharged ratio, ducting ratio and other thermal cycling parameters have great influence on the performance of IRA. Reasonable application of intercooling and reheating technology and optimization of engine thermal cycling parameters can significantly improve the performance of the engine.