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research-article

Transonic Compressor Blade Optimization Integrated with Circumferential Groove Casing Treatment

[+] Author and Article Information
Weimin Song

School of Aerospace Engineering, Tsinghua University, Beijing, 100084, People's Republic of China
songweimin1989@163.com

Yufei Zhang

School of Aerospace Engineering, Tsinghua University, Beijing, 100084, People's Republic of China
zhangyufei@tsinghua.edu.cn

Haixin Chen

School of Aerospace Engineering, Tsinghua University, Beijing, 100084, People's Republic of China
chenhaixin@tsinghua.edu.cn

Kaiwen Deng

School of Aerospace Engineering, Tsinghua University, Beijing, 100084, People's Republic of China
dkw_2105@163.com

1Corresponding author.

ASME doi:10.1115/1.4041699 History: Received April 28, 2018; Revised October 06, 2018

Abstract

A compressor blade integrated with circumferential groove casing treatment (CGCT) is optimized in this study. A hybrid aerodynamic optimization algorithm that combines the differential evolution with a radial basis function response surface is used to search the multi-objective optimized results via the computational fluid dynamics analysis. The sweep and lean distributions are optimized to pursue the maximum total pressure ratio and adiabatic efficiency at the design point. Constraints on the choking mass flow rate and the near-stall compression ratio are applied to ensure the off-design performance. The performance is improved much more with the blade-CGCT integrated optimization than with the blade-only optimization. The stall margin of the blade-only optimized blade with CGCT added later can be even worse than the baseline blade. The CGCT-removal test for the blade-CGCT optimization result further verifies that the performance of the integrated optimization is enhanced via the optimized coupling between the redistributed spanwise loading and the flow control effects of the CGCT. The influence of the three-dimensional stacking line design on the loading redistribution is also studied.

Copyright (c) 2018 by ASME
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