可控扩散叶型吸力面峰值等熵马赫数位置对叶栅气动性能影响  

Effect of Positions of Peak Isentropic Mach Number on Suction Surface of Controlled Diffusion Airfoils on Aerodynamic Performance of Cascades

作　　者：陈晓洁 周正贵[1] 曾凌霄 CHEN Xiaojie;ZHOU Zhenggui;Zeng Lingxiao(College of Energy and Power Engineering,Nanjing University of Aeronautics and Astronautics,Nanjing 210016,China)

机构地区：[1]南京航空航天大学能源与动力学院,江苏南京210016

出　　处：《机械制造与自动化》2024年第2期106-111,共6页Machine Building & Automation

基　　金：国家科技重大专项项目(2017-II-0001-0013)。

摘　　要：通常亚音压气机叶型表面等熵马赫数分布符合可控扩散规律,并且吸力面峰值马赫数位置靠前叶栅气动性能较好。采用自动优化方法,设计出给定吸力面峰值等熵马赫数位置可控扩散叶型,分析此位置对叶栅气动性能的影响规律。研究结果表明:对于可控扩散转子和静子叶型,在设计工况下,当吸力面峰值等熵马赫位置位于0.20倍轴向弦长时,吸力面附面层沿流程快速发展,造成叶栅损失大幅增加;当吸力面峰值等熵马赫数位置为0.10~0.15倍轴向弦长时,设计进气角近似位于叶栅低损失进气角范围中,且低损失范围内损失较低。The isentropic Mach number distribution on the airfoil surface of a subsonic compressor generally complies with the law of controlled diffusion,and the aerodynamic performance of cascades in front peak Mach number position on the suction surface is satisfactory.Designs a controlled diffusion airfoils with given suction surface peak isentropic Mach number position by automatic optimization technique,and analyzes the effect of its positions on the aerodynamic performance of the cascades.The results show that the controlled diffusion rotor and stator airfoils,when the peak isentropic Mach position of the suction surface is 0.20,times the axial chord length under the design condition,the boundary layer of the suction surface develops rapidly along the flow,resulting in a large increase in cascade loss.When the position of the peak isentropic Mach number on the suction surface is ranging from 0.10 to 0.15 times the axial chord length,the inlet angle at design point is approximately in the middle of the operating range,and lower loss is expected in the operating range.

关 键 词：压气机 叶栅 负载分布 可控扩散叶型 优化设计 

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]