核心机派生间冷回热航空发动机热循环参数匹配研究

Research on Thermodynamic Cycle Parameter Matching for Core-derivative Intercooled Recuperated Aero-engine

间冷回热航空发动机作为一种新概念动力技术,可满足未来民用航空发动机对成本控制、环境友好性等方面的要求。以成熟的核心机为基础,在常规热力循环基础上增加间冷过程和回热过程,匹配低压系统派生间冷回热涡扇发动机,进行热力循环参数选择与性能仿真分析。结果表明,派生的间冷回热航空发动机性能提升明显,与常规循环发动机相比,净推力增加14.85%,耗油率降低14.02%;风扇外涵压比、涵道比、增压机压比、间冷度、回热度、外涵间冷用气量等参数对IRA性能有很大影响,合理优化热力循环参数匹配可以显著改善发动机性能。研究结果为后续间冷回热航空发动机的方案论证与开展提供了参考。

As a new concept of power technology,the intercooled recuperated Aero-engine(IRA)could meet demands on the cost and environmental-friendliness in the fields of civil aero-engine.The intercooled and recuperated processes are incorporated into the conventional turbofan engine thermodynamic cycle,then the IRA could be derived based on mature gas turbine core-engine by matching low-pressure system.Thermodynamic cycle parameters choosing and performance simulation are carried out under this model.The results indicate that the specific fuel consumption is reduced to 14.02% while the net thrust is increased to 14.85% compared with conventional turbofan.Thermodynamic cycle parameters such as fan pressure ratio,bypass ratio,booster pressure ratio,intercooler effectiveness,recuperator effectiveness and bypass intercooling split have significant influence on IRA performance,which can be improved with the optimized matching.It provides reference for the subsequent scheme formulation and implementation of IRA.