热膜测试技术在涡轮叶栅边界层测量中的应用

推进技术 ›› 2014, Vol. 35 ›› Issue (9): 1227-1233.

热膜测试技术在涡轮叶栅边界层测量中的应用

庄纯青,刘火星

北京航空航天大学能源与动力工程学院航空发动机气动热力国防科技重点实验室，北京 100191;北京航空航天大学能源与动力工程学院航空发动机气动热力国防科技重点实验室，北京 100191

发布日期:2021-08-15
作者简介:庄纯青(1987—)，男，硕士生，研究领域为附面层流动特性实验。

Boundary Layer Research of Turbine Blade Based on

National Key Laboratory of Aircraft Engine，School of Jet Propulsion，Beihang University，Beijing 100191，China;National Key Laboratory of Aircraft Engine，School of Jet Propulsion，Beihang University，Beijing 100191，China

Published:2021-08-15

摘要/Abstract

摘要： 为了更加精确地测量附面层流动状态，并验证表面热膜测试技术的可靠性，利用表面热膜测量了低雷诺数定常来流条件下高负荷涡轮叶栅通道内叶片吸力面附面层的流动状态，并与表面静压实验测得结果进行对比。结果表明，利用表面热膜测得的准壁面剪切力以及相关的统计参数能够准确捕捉到附面层分离泡和转捩的位置，对于高负荷低压涡轮叶型附面层流动测量是可靠有效的。

关键词: 表面热膜；高负荷；低压涡轮；分离；转捩

Abstract: In order to research boundary layer separation behaviors more accuratly and to prove that the surface hot-film testing technique is reliable，a hot-film experimental investigation on steady low Reynolds number boundary layer separation behaviors of the suction surface of a high-loaded low-pressure turbine blade was described，which was compared with the static pressure experimentation. The experimental results indicate that the quasi-shear stress and the statistical value of the surface hot-film can capture the position of separation bubble and transition accurately. The surface hot-film technique is effective and reliable for measurement on the high-load low-pressure turbine blade.

Key words: Surface hot-film；High-load；Low-pressure turbine；Separation；Transition

庄纯青,刘火星. 热膜测试技术在涡轮叶栅边界层测量中的应用[J]. 推进技术, 2014, 35(9): 1227-1233.

ZHUANG Chun-qing,LIU Huo-xing. Boundary Layer Research of Turbine Blade Based on[J]. Journal of Propulsion Technology, 2014, 35(9): 1227-1233.

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