考虑多工况性能可靠性的航空发动机循环设计方法

Aero-engine cycle design approach for multiple operating conditions performance reliability

为实现航空发动机总体性能设计方法由传统的确定性设计向不确定性概率设计转变,提出基于分布式协同响应面法思想的航空发动机多工况性能可靠性循环优化设计方法:建立了引入非确定性部件性能的航空发动机性能仿真模型,通过试验设计、非设计点性能仿真试验等步骤,构建了各典型工况下发动机推力与耗油率性能可靠度关于设计点循环参数的分布式响应面模型,并以此构建多工况性能协同响应面模型进行循环参数优化设计,最终获得循环参数非劣解集并通过随机试验进行验证。结果表明,通过多工况性能可靠性循环优化设计方法获得的循环参数非劣解集均能使发动机在多个典型工况下的总体性能同时达到不低于97.5%的高可靠度,为设计人员根据实际情况选取循环参数提供依据。

In order to evolve aeroengine overall performance design from the deterministic design to the probabilistic design,an aeroengine cycle optimization design approach for multiple operating conditions performance reliability based on distributed cooperative response surface method(DCRSM)was proposed.The turbofan engine simulation model with uncertainty component performance was established as an example.The distributed response surface models of thrust and special fuel consumption performance under several typical operating conditions were established by the experimental design and the off design point performance simulation,and then the cooperative response surface model was established for cy-cle optimization.The non inferiority solution set of the cycle parameters was generated from optimization and verified by the random trial.The results showed that the all cycle parameters from the non inferiority solution set could make the engine overall performance achieve a high reliability of not less than 97.5% simultaneously under all expected operating conditions.From the non inferiority solution set obtained by multiple operating conditions performance reliability cycle optimization method,the most suitable cycle selection can be decided according to the physical truth in engine preliminary design phase.