跨声速压气机动叶平面叶栅实验  

Experiment on rotor plane cascade of transonic compressor

作　　者：高宇[1] 钟兢军[1] 李晓东[1] 杨凌[1] 

机构地区：[1]大连海事大学轮机工程学院,辽宁大连116026

出　　处：《航空动力学报》2016年第5期1178-1185,共8页Journal of Aerospace Power

基　　金：国家自然科学基金重点项目(51436002);国家自然科学基金(51506020);中央高校基本科研业务费专项资金(3132016205);辽宁省高等学校创新团队项目(LT2015004);辽宁省自然科学基金(2015020636)

摘　　要：对某跨声速压气机动叶根部叶型平面叶栅流场在不同冲角和进口等熵马赫数下进行了详细的测量,得到了冲角特性曲线和叶片表面及端壁静压.结果表明:负冲角及零冲角时,叶栅出口总压损失系数随进口等熵马赫数增加变化不大,而在正冲角时变化较大.相同进口等熵马赫数下,负冲角和零冲角时,叶片负荷较高;正冲角时,由于气流分离严重,叶片负荷下降,叶栅出口总压损失系数升高.随冲角由负冲角向正冲角增加,气流落后角逐渐增大,叶栅出口总压损失系数先减小后增大,最小值为0.034.冲角相同时,随进口等熵马赫数增加,叶栅出口总压损失系数总体呈增加趋势.The flow field of plane cascade with the blade root profile of a transonic com- pressor rotor was surveyed in detail at different incidences and inlet isentropic Mach num hers, and the characteristic curve of incidence and the static pressure coefficients of blade surface and end wall were gained. Results showed that the total pressure loss coefficients at the cascade outlet changed a little with different inlet isentropic Mach numbers at negative and zero incidences, and changed largely at positive incidences. With the same inlet isentropic Mach number, the blade load was high at negative and zero incidences, and decreased due to the flow separation, but the total pressure loss coefficients at the cascade outlet increased at positive incidences. With the increase of incidence, the stagger angle increased, and the total pressure loss with the minimum value of 0. 034 slowed down and then up. With the increase of inlet isentropic Mach numbers, the total pressure loss coefficients at the cascade outlet increased at the same incidence.

关 键 词：跨声速压气机 平面叶栅 流场特性 冲角 实验测量 

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]