某型涡桨发动机气动热力仿真计算  

Aerothermodynamic Simulation Calculation of a Certain Turboprop Engine

作　　者：盛柏林 李琼 伍恒[2] 张勇[2] 

机构地区：[1]中国南方航空工业(集团)有限公司产品设计所,湖南株洲412002 [2]海军航空工程学院飞行器工程系,山东烟台264001

出　　处：《海军航空工程学院学报》2016年第2期121-126,共6页Journal of Naval Aeronautical and Astronautical University

基　　金：国家自然科学基金资助项目(51505492)

摘　　要：文章计算了各气路部件之间的气动热力参数和总体性能参数大小,分析相互关系,进而对发动机的设计提供理论依据。针对某型涡桨发动机的气路结构进行了气动热力仿真计算研究,利用设计手册给定的发动机设计点主要工作参数数据进行气动热力仿真计算,对比计算得到的发动机总体性能参数数据与设计点给定的总体性能参数数据,验证了仿真计算算法的有效性以及准确性。针对气动热力仿真计算结果所产生的误差,初步分析并验证了算法优化需要考虑的部件特性的耦合系数以及引气对发动机性能的影响等因素。In order to study the aerothermodynamic process of a certain turboprop engine, the value of aerothermodynamic parameters and overall performance parameters between each component in gas path was calculated and the relationship between them was analyzed to provide a theoretical basis for engine design. Aerothermodynamic calculation study is performed focusing on the gas path structure of a certain turboprop engine, the main operating parameter data of engine design point given by design manual were used to do aerothermodynamic calculation, comparing the value of calculated overall engine performance parameters with the value of overall performance parameters given by design point to verify the effectiveness and accuracy of the simulation algorithm. Focusing on the error generated by the results of aerothermodynamic calculation, the coupling coefficient of component characteristics and the impact on engine performance of air entraining and other factors, which were needed to consider for algorithm optimization, were preliminary analyzed and verified.

关 键 词：涡桨发动机 气动热力仿真计算 设计点 总体性能参数 算法优化 

分 类 号：V231.1[航空宇航科学与技术—航空宇航推进理论与工程]