涡轴-涡扇变循环发动机方案设计的多设计点融合算法

Fusion algorithm of multi design points for turboshaft-turbofan variable cycle engine scheme design

针对有涡轴和涡扇两种工作模态的涡轴-涡扇变循环发动机,提出了其方案设计的多设计点融合算法。以涡喷发动机为例,对发动机多设计点设计的融合算法模型的建立方法进行了介绍;建立了涡轴-涡扇变循环发动机的多设计点融合算法模型;确定涡轴-涡扇变循环发动机的典型工况点包括高空巡航涡扇模态工况点、地面涡轴模态工况点及转模态工况点,完成发动机方案设计;最后以各典型工况点处飞行器对发动机的性能需求为多设计点融合算法的输入条件,与常规方法得到的参数进行对比验证,结果差异在1%以内。所提出的多设计点融合算法可为变循环发动机总体方案设计提供借鉴。

A fusion algorithm of multi design points(FAMDP)was proposed for the design of turboshaft-turbofan variable cycle engine(TSFVCE)with two operating modes,including:turboshaft mode and turbofan mode.A turbojet engine was taken as an example to introduce the establishment of a FAMDP model.The FAMDP model for the TSFVCE was established.The typical operating points of the TSFVCE,including high-altitude cruise turbofan mode operating points,ground turboshaft mode operating points,and modal conversion operating points,were determined,and the design of the engine scheme was completed.The performance requirements of the aircraft for the TSFVCE at each typical operating point were used as input for the FAMDP.Compared with the parameters obtained by conventional methods,the results showed a difference of less than 1%.The fusion algorithm of multi design points proposed can provide a reference for the overall design of variable cycle engines.