缩扩比对微型跨音轴流涡轮性能的影响研究  

Influence of Convergent-divergent Ratio on Performance of Micro Transonic Axial Turbine

作　　者：孙湘林 夏晨[1] 陈锦文 SUN Xianglin;XIA Chen;CHEN Jinwen(College of Energy and Power Engineering,Nanjing University of Aeronautics and Astronautics,210016 Nanjing,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》2023年第4期56-59,共4页Machine Building & Automation

摘　　要：微型涡轮面临高负荷、跨音速流动的技术挑战,为满足高性能微型发动机的发展需要,采用数值仿真方法对缩扩比及其径向分布规律对微型跨音轴流涡轮性能及流动特性的影响规律进行研究,获得了较佳的缩扩比取值范围及合适的径向分布规律。实验结果表明:对二维叶型而言,通过局部调整吸力面喉道后内伸波入射点前的型线曲率,使缩扩比处于1.04~1.08范围内,可使波前马赫数降低3.4%,并有效抑制内伸波反射,转子总压损失系数最大可降低14.1%;对三维叶片而言,选择两端大、中间小的“C型”缩扩比径向分布规律可使所研究的微型涡轮级效率提升0.45%,流量增大0.66%,并在宽落压比范围内仍保持较高的性能。Micro-turbine is facing the technical challenge of high-load and transonic flow,and in order to meet the needs of the development of high-performance micro-engine,this paper studies the effects of convergent-divergent ratio and its radial distribution on the performance and flow characteristics of the micro transonic turbine,and the good value range of convergent-divergent ratio with appreciate radial distribution law is abtained.The results show that for the cascade,by locally adjusting the profile curvature in front of the incident point of the rear-extension wave in the throat of the suction surface,the convergent-divergent ratio is kept in the range of 1.04—1.08,which can reduce the incoming Mach number of shock waves by 3.4%and suppress the reflection effectively,with total pressure loss coefficient reduction by 14.1%at most.For rotor blades,selecting the radial distribution law of“C-type”convergent-divergent ratio can improve the efficiency of the micro turbine by 0.45%,raise the mass flow by 0.66%,and maintain better performance in a wide working range.

关 键 词：微型跨音轴流涡轮 型线曲率调整 缩扩比 缩扩比径向分布规律 

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]