【摘 要】
：
平面叶栅实验能够直观有效地评定叶型气动性能并验证设计方法,是高性能压气机叶栅设计的重要环节,在叶栅性能基础研究中有重大意义.基于高亚音速叶栅风洞,本文对某压气机原始叶型及其优化叶型进行了平面叶栅实验,对两套叶型的尾迹总压、表面马赫数等参数的分布进行了测量,对比了两套叶型流动特征.实验结果表明:优化叶型对正攻角更敏感,表现出较好的负攻角特性;原始叶型对负攻角更加敏感,表现出较好的正攻角特性;在优化叶
【机 构】
：
西北工业大学动力与能源学院;先进航空发动机协同创新中心
论文部分内容阅读
平面叶栅实验能够直观有效地评定叶型气动性能并验证设计方法,是高性能压气机叶栅设计的重要环节,在叶栅性能基础研究中有重大意义.基于高亚音速叶栅风洞,本文对某压气机原始叶型及其优化叶型进行了平面叶栅实验,对两套叶型的尾迹总压、表面马赫数等参数的分布进行了测量,对比了两套叶型流动特征.实验结果表明:优化叶型对正攻角更敏感,表现出较好的负攻角特性;原始叶型对负攻角更加敏感,表现出较好的正攻角特性;在优化叶型的设计点(1M a=0.7,i=2.5°),优化叶型低总压损失范围较宽且偏向负攻角区域,在0°～2.5°攻角范围总压损失基本不变,其中在设计攻角2.5°时总压损失最低,总压损失系数为8.21％,比原始叶型减少了1.08％;在原始叶型的设计点(1M a=0.5,i=2.5°),优化叶型总压损失有较小增加,但是低总压损失范围向负攻角方向明显扩宽.当进口马赫数超过0.7后,原始叶型总压损失急剧增大,可以预判气流已经分离,而优化叶型的损失增加较为平缓,原始叶型受马赫数影响更加显著.原始叶型在整个轴向弦长范围内静压更低,表面等熵马赫数更高,叶片气动负荷更大,优化叶型由于前缘吸力面加速较快,实验测量时并未捕捉到吸力面加速的过程,但优化叶型减速扩压过程更缓.
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