Effect of the distribution of the upstream probe support on performance of compressor cascade
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Kuanxin Hou
,
Jie Gao
Abstract
Aiming at the problem of aerodynamic coupling interference between disturbance of the built-in measurement probe and internal flow of high load compressor, the experiment of axial position and structure dimension of cylindrical probe support effect on the performance of the compressor cascade was carried out on the transonic plane cascade test facility. The effect characteristics of the distribution of probe support on aerodynamic performance of downstream cascade under different inlet Mach numbers were analyzed through the experimental data. The experimental results show that the axial position of probe support has little impact on the total pressure loss coefficient of cascade under the low-speed inlet flow condition. However, the variety of the axial position of probe support has a great impact on the total pressure loss coefficient of cascade under the high-speed inlet flow condition. With the decrease of the axial distance between probe support and cascade, the total pressure loss coefficient of cascade increases. Under different inlet flow conditions, the variety of the structure dimension of probe support has a significant impact on the total pressure loss coefficient of cascade. With the increase of the structure dimension of probe support, the total pressure loss coefficient of cascade increases.
Funding source: Sichuan Province Science and Technology Innovation Talent Project
Award Identifier / Grant number: 2022JDRC0013
Funding source: Advanced Aviation Power Innovation Workstation Project
Award Identifier / Grant number: HKCX2022-01-022
Funding source: Civil Aircraft Special Scientific Research Project
Award Identifier / Grant number: MJ-2016-J-96
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Author contributions: All the authors have accepted responsibility for the entire content of this submitted manuscript and approved submission.
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Research funding: This research work has been supported by the Sichuan Province Science and Technology Innovation Talent Project (Grant No. 2022JDRC0013), Advanced Aviation Power Innovation Workstation Project (Grant No. HKCX2022-01-022) and Civil Aircraft Special Scientific Research Project (Grant No. MJ-2016-J-96). The authors would like to express their gratitude to Sichuan Gas Turbine Establishment of Aero Engine Corporation of China for its support and permission to publish this paper.
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Conflict of interest statement: The authors declare no conflicts of interest regarding this article.
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