论文部分内容阅读
采用叶栅吹风试验与数值模拟相结合的方法,研究了攻角变化对具有较大前缘半径和进口楔角的透平叶栅气动性能的影响,试验测量在出口马赫数为0.8、攻角-61.0°~+4.0°内进行,对应的雷诺数为6.0×105.在试验验证数值方法可靠性的基础上,对叶栅流动损失进行了数值研究,分析了攻角变化对试验叶栅型面损失中吸力面与压力面边界层损失、尾迹损失和端部次流的影响特性.结果表明:当攻角从+4.0°变化到-41.0°时,叶片表面没有发生流动分离,出口截面的总压损失系数变化幅度不超过0.21%;在负攻角很大(-61.0°)时,压力面边界层发生流动分离,型面损失急剧增大;具有较大前缘半径和进口楔角的试验用叶栅表现出良好的变攻角气动性能.
The effect of angle of attack on the aerodynamic performance of turbine cascade with large leading edge radius and inlet wedge angle was studied by using the combination of cascade blowing test and numerical simulation. The experimental measurements were carried out at an outlet Mach number of 0.8 and an angle of attack -61.0 ° ~ + 4.0 °, the corresponding Reynolds number is 6.0 × 105. Based on the experimental verification of the reliability of the numerical method, the cascade flow losses are numerically studied, The loss of boundary layer on the suction side and the pressure side, the loss of wake and the influence of the end flow on the surface loss are analyzed.The results show that no flow separation occurs on the blade surface when the angle of attack changes from + 4.0 ° to -41.0 °, The total pressure loss coefficient does not change more than 0.21%. When the negative angle of attack is large (-61.0 °), the boundary layer of the pressure surface is separated and the loss of profile increases sharply. With the large leading edge radius and the inlet wedge angle The experimental cascade shows a good aerodynamic performance at variable angle of attack.