涡轮叶片气动性能影响因素的实验与数值研究  

Influence on Aerodynamic Performance of Turbine Cascade by Experiment and Numerical Simulation

作　　者：马一鸣[1] 王建飞[1] 臧述升[1] 

机构地区：[1]上海交通大学叶轮机械研究所,上海200240

出　　处：《燃气轮机技术》2013年第4期23-27,共5页Gas Turbine Technology

摘　　要：本文利用实验与数值模拟的方法研究航空发动机涡轮叶栅在改变节距时，其总压损失、出口气流角及叶栅表面静压系数的变化。通过实验和数值计算的结果对比，验证了数值计算的准确性。数值模拟结果显示：相对节距t在0．5—1．0范围内变化，叶栅的总压损失在t=0．9时达最小；叶栅人口攻角从-10°逐渐增加至＋10°时，总压损失呈现递增的趋势；随着相对节距每增加0．1，气流出口角相应增加大约2°；随着叶栅相对节距的增加，附面层增厚、脱离，叶型损失增大。In this paper, cascade pitch is changed to find out the trend of total pressure, exit flow angle and surface static pressure coefficient by experiment and numerical simulation. Contrast experiment result with numerical simulation, prove that numerical simulation is correct. The result of simulation show：Relative pitches of cascade are changed from 0. 5 to 1.0 and find out that total pressure loss has a best result when relative pitch t = 0. 9 ; When angle of attack is increased from - 10° to ＋ 10°, the total pressure loss also increases ; Flow exit angle increases 2°with each 0. 1 increase in relative pitch ; With the increasing of relative pitch, boundary layer become thicker and separate from the cascade, profile loss increases.

关 键 词：涡轮 稠度 总压损失 静压系数 

分 类 号：TK14[动力工程及工程热物理—热能工程]