弯度比对高负荷微型跨音轴流涡轮性能的影响分析  

Influence of Camber Ratio on Performance of High-Load Micro Transonic Axial Turbine

作　　者：李俊 夏晨[1] 黄国平[1] LI Jun;XIA Chen;HUANG Guoping(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》2022年第3期48-51,84,共5页Machine Building & Automation

摘　　要：在当前微型涡轮发动机中,其核心部件涡轮普遍存在单位级负荷较低现象,限制了发动机总体性能。为适应高性能微型涡轮发动机发展,开展高负荷微型跨音轴流涡轮设计与分析,采取CFD数值仿真方法研究弯度比叶型参数对性能的规律性影响。研究表明:单位级负荷增大会造成叶根气流分离变大,叶型损失和叶尖泄漏损失增加。低弯度比易造成前缘叶背分离及负载荷;高弯度比易造成尾缘分离及负载荷。当弯度比介于0.30~0.35之间时,该高负荷微型跨音轴流涡轮会呈现较好的性能和做功能力。In order to adapt to the development of high-performance micro-turbine engines,whose current micro-turbine engine with its low unit-level load core component turbine limiting the overall performance,high-load micro transonic axial turbines are designed and analyzed,and CFD numerical simulation methods are applied to study the influence of camber ratio on the regularity of performance.The results show that the increase of unit load will bring about the increase of airflow separation and the losses of both blade profile and the tip leakage.Low camber ratio is easy to cause separation of leading edge blade back and negative load while high camber ratio is likely to lead to trailing edge separation and negative load.When the camber ratio is between 0.30-0.35,the high-load micro transonic axial turbine presents better performance and power ability.

关 键 词：微型涡轮发动机 高负荷 流动损失 弯度比 

分 类 号：V235.1[航空宇航科学与技术—航空宇航推进理论与工程]