跨声速压气机动叶平面叶栅实验

发布时间：2018-01-15 18:38

本文关键词：跨声速压气机动叶平面叶栅实验　出处：《航空动力学报》2016年05期 　论文类型：期刊论文

【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.
[Abstract]:The flow field at the root of a transonic compressor is measured in detail under different incidence angles and inlet Isentropic Mach numbers. The angle characteristic curve and the static pressure on the blade surface and end wall are obtained. The results show that the total pressure loss coefficient of the cascade outlet does not change with the increase of the inlet Isentropic Mach number when the angle of incidence is negative and the incidence angle is zero. At the same inlet Isentropic Mach number, the blade load is higher when the incidence angle is negative and zero incidence angle is the same as the same inlet Isentropic Mach number. When the angle of incidence is positive, due to the serious separation of air flow, the blade load decreases and the total pressure loss coefficient of cascade outlet increases. With the increase of the angle of incidence from negative angle of incidence to positive angle of incidence, the backward angle of airflow increases gradually. The total pressure loss coefficient of the cascade outlet decreases first and then increases, and the minimum value is 0.034. When the incidence angle is the same, the total pressure loss coefficient of the cascade outlet increases with the increase of the inlet Isentropic Mach number.
【作者单位】：大连海事大学轮机工程学院;
【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)
【分类号】：V233
【正文快照】： 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)为提高压气机单级压比,减少多级压气机的级数,现代燃气轮机压气机叶片多采用高负荷叶型[1-3].与亚声速压气机和超声速压气机相比,跨声速压气机由于可以同时

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