摘要
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．
Abstract
The intercooled and recuperated processes were incorporated into the conventional high bypass turbofan engine thermodynamic cycle. Consequently, the intercooled recuperated aero-engine （IRA） simulation model was built and an overall performance simulation program was developed. Then, analysis on choosing and matching the thermodynamic cycle parameters of IRA was conducted. The result indicates that there are some thermody- namic cycle parameters such as intercooler effectiveness, recuperator effectiveness, bypass intercooling split, pressure ratio assignment between booster and high pressure compressor, overall pressure ratio and bypass ratio, which have significant influence on IRA performance. The turbofan engine performance can be improved with the proper use of intercooling, recuperation and the optimized matching of the thermodynamic cycle parameters.
基金项目
国家自然科学基金(51176156)
教育部高等学校博士学科点专项科研基金(20106102110025)
NETL
NSTL
维普
万方数据