In order to meet the need of using simulation models in the stages of aircraft engine model design and airworthi-ness certification to quickly and effectively calculate the impact of intake distortion on engine performance,a study is con-ducted on the calculation method of engine overall performance based on parallel compressor model.On the basis of a general simulation system for engine performance,parallel compressor component classes are constructed through inheri-tance,association,and other methods;using the iterative calculation parameters of performance simulation model of the entire as the boundary constraint for the outlet of the sub-compressor,the operating point of the sub-compressor are itera-tively calculated to obtain the compressor,engine operating points,and overall engine performance;a certain type of hy-brid exhaust afterburner dual rotor turbofan engine is used as the simulation object to calculate the design point perfor-mance and the off-design point performance under inlet distortion conditions,verifying the effectiveness of the calcula-tion method and analyzing the impact of inlet distortion on the overall performance of the compressor and engine.
国家科技期刊平台
NSTL
维普
万方数据
