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2024 , Vol. 33 >Issue 1: 158 - 171

DOI: https://doi.org/10.1007/s11630-023-1929-1

Experimental and Numerical Investigations of Shock-Wave Boundary Layer Interactions in a Highly Loaded Transonic Compressor Cascade

  • MENG Fanjie ,
  • LI Kunhang ,
  • GUO Penghua ,
  • GAN Jiuliang ,
  • LI Jingyin
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  • 1. School of Energy and Power Engineering, Xi’an Jiaotong University, Xi’an 710049, China
    2. Institute of Engineering Thermophysics, Chinese Academy of Sciences, Beijing 100190, China

网络出版日期: 2024-01-16

基金资助

This work has been supported by National Science and Technology Major Project (2017-II-0007-0021).

版权

Science Press, Institute of Engineering Thermophysics, CAS and Springer-Verlag GmbH Germany, part of Springer Nature 2023
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Experimental and Numerical Investigations of Shock-Wave Boundary Layer Interactions in a Highly Loaded Transonic Compressor Cascade

  • MENG Fanjie ,
  • LI Kunhang ,
  • GUO Penghua ,
  • GAN Jiuliang ,
  • LI Jingyin
Expand
  • 1. School of Energy and Power Engineering, Xi’an Jiaotong University, Xi’an 710049, China
    2. Institute of Engineering Thermophysics, Chinese Academy of Sciences, Beijing 100190, China

Online published: 2024-01-16

Supported by

This work has been supported by National Science and Technology Major Project (2017-II-0007-0021).

Copyright

Science Press, Institute of Engineering Thermophysics, CAS and Springer-Verlag GmbH Germany, part of Springer Nature 2023
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摘要

本文采用实验和数值计算相结合的方法研究了高负荷跨音速压气机叶栅中激波边界层相互作用（SBLI）现象。试验过程中采用 纹影技术捕捉叶栅中的激波结构，并使用压力探针测量叶片表面的静压分布。同时，采用快速响应压力敏感漆（PSP）技术测量了整个叶片表面的非定常压力分布，捕捉到了 SBLI 引起的激波振荡特征。此外，采用三维RANS对跨音速叶栅中的定常流场进行了数值模拟。结果发现，随着马赫数的增加，设计状态下SBLI现象发生明显的变化，尤其是在 SBLI 引起的分离气泡存在的情况下。值得注意的是，在马赫数为 0.85 时， PSP 技术测量的叶片表面时均压力场呈对称分布，而在马赫数为 0.90 和 0.95 时则呈非对称分布。通过分析PSP瞬态结果发现，激波低频振荡现象与叶片表面的分离泡密切相关，振幅几乎可以横跨一个压力探孔间隔，因此激波的振荡可能会影响到压力探针对于激波位置处压力突变的捕捉。

关键词： transonic flow; transonic compressor cascade; shock-wave boundary-layer interaction; shock oscillation

本文引用格式

MENG Fanjie , LI Kunhang , GUO Penghua , GAN Jiuliang , LI Jingyin . Experimental and Numerical Investigations of Shock-Wave Boundary Layer Interactions in a Highly Loaded Transonic Compressor Cascade[J]. 热科学学报, 2024 , 33(1) : 158 -171 . DOI: 10.1007/s11630-023-1929-1

Abstract

Experimental and numerical investigations were conducted to investigate the variations of shock-wave boundary layer interaction (SBLI) phenomena in a highly loaded transonic compressor cascade with Mach numbers. The schlieren technique was used to observe the shock structure in the cascade and the pressure tap method to measure the pressure distribution on the blade surface. The unsteady pressure distribution on blade surface was measured with the fast-response pressure-sensitive paint (PSP) technique to obtain the unsteady pressure distribution on the whole blade surface and to capture the shock oscillation characteristics caused by SBLI. In addition, the Reynolds Averaged Navier Stokes simulations were used to compute the three-dimensional steady flow field in the transonic cascade. It was found that the shock wave patterns and behaviors are affected evidently with the increase in incoming Mach number at the design flow angle, especially with the presence of the separation bubble caused by SBLI. The time-averaged pressure distribution on the blade surface measured by PSP technique showed a symmetric pressure filed at Mach numbers of 0.85, while the pressure field on the blade surface was an asymmetric one at Mach numbers of 0.90 and 0.95. The oscillation of the shock wave was closely with the flow separation bubble on the blade surface and could transverse over nearly one interval of the pressure taps. The oscillation of the shock wave may smear the pressure jump phenomenon measured by the pressure taps.

Key words： transonic flow; transonic compressor cascade; shock-wave boundary-layer interaction; shock oscillation

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