轴流压气机平面叶栅气动特性的数值研究

Numerical study on aerodynamic characteristics of axial compressor cascade

以轴流压气机DMU37动叶根部5%叶高典型截面叶型为研究对象,采用Fluent软件,计算分析不同冲角和进口等熵马赫数下叶栅流场损失及气动特性.结果表明:同一冲角下,进口等熵马赫数的提高增加了叶片负荷和扩压能力,同时也使出口总压损失增加,失速冲角范围变小;相同进口马赫数时,随着冲角增加,出口总压损失先减小后增大,-4°冲角时总压损失最小.同时,验证了轴流压气机平面叶栅马赫数、冲角损失特性规律具有相似性,并且,叶栅端壁区域受进口马赫数和冲角变化影响较大.

The axial compressor DMU37 rotor blade 5% typical section blade was taken as the study object,the outlet flow field loss and aerodynamic characteristics of the cascade under different incidence angle and inlet isentropic Mach numbers were calculated and analyzed by using Fluent software. Results show that under the same impact angle,the increase of the inlet isentropic Mach number increases the blade load and the capacity of expanding pressure,but also increase the outlet total pressure loss,and the stall angle becomes smaller.For the same inlet Mach number,the total pressure loss at the outlet decreases first and then increases with the increase of the incidence angle,and the total pressure loss at the angle of-4° is the smallest. At the same time,it is verified that the loss characteristics of inlet isentropic Mach number and incidence angle of the axial compressor cascade are similar. Besides,the influence of change of the inlet Mach number and the angle of incidence on the wall area is lager.