海军航空大学学报2024，Vol.39Issue(2)：249-260,12.DOI:10.7682/j.issn.2097-1427.2024.02.008
基于平行压气机模型的发动机整机性能计算方法
Calculation Method of Engine Overall Performance Based on Parallel Compressor Model
摘要
Abstract
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.关键词
平行压气机模型/进气畸变/性能仿真/航空发动机Key words
parallel compressor model/inlet distortion/performance simulation/aeroengine分类
航空航天引用本文复制引用
史永运,宋汉强,张赟,邵仁,迟雅琴,李朋..基于平行压气机模型的发动机整机性能计算方法[J].海军航空大学学报,2024,39(2):249-260,12.基金项目
国家自然科学基金(51505492) （51505492）
