Calculation Method of Engine Overall Performance Based on Parallel Compressor Model
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
万方数据
维普
