低速轴流压气机转子叶片三维优化的数值研究  

Numerical study on three-dimensional optimization of low-speed axial compressor rotor blade

作　　者：张晨凯[1] 胡骏[1,2] 王志强[1] 尹超[1] 严伟[1] 

机构地区：[1]南京航空航天大学能源与动力学院江苏省航空动力系统重点实验室,南京210016 [2]先进航空发动机协同创新中心,北京100191

出　　处：《航空动力学报》2015年第2期483-490,共8页Journal of Aerospace Power

基　　金：高等学校博士学科点专项科研基金(20123218120009)

摘　　要：为了深入认识低速大尺度轴流压气机端壁区的流动,减小流动损失,提高其气动性能,采用数值模拟和优化相结合的手段,针对用于低速模拟的某低速大尺度轴流压气机原型转子的三维积叠线进行了优化,提高了其设计工况下的气动性能.结果表明:优化转子轮毂附近无法承受过大的负荷;相比于原型转子,优化转子主要的性能提升位于轮毂附近,一定程度的正弯有效减小了轮毂区的流动损失,具有"前加载"的效果,抑制了叶根尾缘的流动分离,转子总压损失减小约19.4%.To deepen the knowledge of endwall flow in the large-scale low-speed axial compressor,reduce accordingly its flow loss and improve its aerodynamic performance,numerical simulation and optimization were presented.With numerical tool,three-dimensional stacking principle was optimized to improve the design operation point aerodynamic performance for the prototype rotor of a large-scale low-speed axial compressor in low speed simulation.Results show that,near-hub region of the optimized rotor cannot undertake large blade loading;compared with the prototype rotor,the main region of performance improvement of optimized rotor locates near the hub region,and a certain degree of positive bend in this region effectively helps to reduce its flow loss.It shows the effect of＂loaded leading edge＂,which suppresses flow separation near the trailing edge;consequently nearly 19.4% of total pressure loss is reduced.

关 键 词：压气机转子 流动损失 气动性能 数值优化 流动分离 

分 类 号：V231.3[航空宇航科学与技术—航空宇航推进理论与工程]