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Volume 11
Issue 4
10.3390/aerospace11040246
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Article

Performance Improvement of a High Loading Centrifugal Compressor with Vaned Diffuser by Hub Contour Optimization

by
Yunfeng Wu
1,2,3,
Qingkuo Li
4,
Hang Yuan
1,2,3,
Ziliang Li
1,2,3,
Shiji Zhou
1,2,3,
Ge Han
1,2,3 and
Xingen Lu
1,2,3,*
1
National Key Laboratory of Science and Technology on Advanced Light-Duty Gas Turbine, Chinese Academy of Sciences, Beijing 100190, China
2
Key Laboratory of Light-duty Gas-turbine/Institute of Engineering Thermophysics, Chinese Academy of Sciences, Beijing 100190, China
3
School of Aeronautics and Astronautics, University of Chinese Academy of Sciences, Beijing 100190, China
4
Department of Mechanical, Manufacturing and Biomedical Engineering, Trinity College Dublin, Parsons Building, College Green, D02 PN40 Dublin, Ireland
*
Author to whom correspondence should be addressed.
Aerospace 2024, 11(4), 246; https://doi.org/10.3390/aerospace11040246
Submission received: 21 February 2024 / Revised: 16 March 2024 / Accepted: 19 March 2024 / Published: 22 March 2024
(This article belongs to the Special Issue Progress in Turbomachinery Technology for Propulsion)
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Abstract

High-pressure ratio centrifugal compressors’ diffusers face challenges from high-velocity, non-uniform flow at the impeller outlet, decreasing efficiency and stall margin. To address this, this paper presents a novel vaned diffuser passage design method that successfully improved the compressor’s performance. An optimization method using axisymmetric hub contours and NURBS curves was applied to modify the diffuser’s design. After optimization, centrifugal compressor peak efficiency increased by 0.78%, and stall margin expanded from 12.8% to 20.4%. Analysis at the peak efficiency point showed loss reduction mainly from decreased recirculation and mixing losses in the diffuser’s vaneless and semi-vaneless spaces. Furthermore, correlation analysis and Mach number distribution revealed that flow behavior at the diffuser’s leading edge significantly influences efficiency. Consequently, design principles emphasize satisfying specific Mach number distribution rules at the diffuser’s leading edge under certain inflow conditions for optimal performance.
Keywords: high-loading centrifugal compressor; aerodynamic optimization; axisymmetric hub contour; wedge diffuser; entropy loss high-loading centrifugal compressor; aerodynamic optimization; axisymmetric hub contour; wedge diffuser; entropy loss

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MDPI and ACS Style

Wu, Y.; Li, Q.; Yuan, H.; Li, Z.; Zhou, S.; Han, G.; Lu, X. Performance Improvement of a High Loading Centrifugal Compressor with Vaned Diffuser by Hub Contour Optimization. Aerospace 2024, 11, 246. https://doi.org/10.3390/aerospace11040246

AMA Style

Wu Y, Li Q, Yuan H, Li Z, Zhou S, Han G, Lu X. Performance Improvement of a High Loading Centrifugal Compressor with Vaned Diffuser by Hub Contour Optimization. Aerospace. 2024; 11(4):246. https://doi.org/10.3390/aerospace11040246

Chicago/Turabian Style

Wu, Yunfeng, Qingkuo Li, Hang Yuan, Ziliang Li, Shiji Zhou, Ge Han, and Xingen Lu. 2024. "Performance Improvement of a High Loading Centrifugal Compressor with Vaned Diffuser by Hub Contour Optimization" Aerospace 11, no. 4: 246. https://doi.org/10.3390/aerospace11040246

APA Style

Wu, Y., Li, Q., Yuan, H., Li, Z., Zhou, S., Han, G., & Lu, X. (2024). Performance Improvement of a High Loading Centrifugal Compressor with Vaned Diffuser by Hub Contour Optimization. Aerospace, 11(4), 246. https://doi.org/10.3390/aerospace11040246

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