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research-article

A Novel 1D-3D Coupled Method to Predict Surge Boundary of Centrifugal Compressors

[+] Author and Article Information
Meijie Zhang

ASME Membership, Turbomachinery Laboratory, State Key Laboratory of Automotive Safety and Energy, Tsinghua University, Beijing 100084, China
zhang-mj15@mails.tsinghua.edu.cn

Xinqian Zheng

ASME Membership, Turbomachinery Laboratory, State Key Laboratory of Automotive Safety and Energy, Tsinghua University, Beijing 100084, China
zhengxq@tsinghua.edu.cn

Qiangqiang Huang

Turbomachinery Laboratory, State Key Laboratory of Automotive Safety and Energy, Tsinghua University, Beijing 100084, China
hqq14@tsinghua.org.cn

Zhenzhong Sun

Turbomachinery Laboratory, State Key Laboratory of Automotive Safety and Energy, Tsinghua University, Beijing 100084, China
sunzz14@mails.tsinghua.edu.cn

1Corresponding author.

ASME doi:10.1115/1.4042419 History: Received June 26, 2018; Revised December 24, 2018

Abstract

Compression systems are widely employed in gas turbine engines, turbocharged engines and industry compression plants. The stable work of compression systems is an essential precondition for engine performance and safety. A compression system in practice usually consists of upstream and downstream pipes, compressors, plenums and throttles. When a compression system encounters the surge, the flows in the compressor present complex three-dimensional patterns but the flows of other components might present relatively simple one-dimensional patterns. Based on these flow characteristics, this paper proposes a novel simulation method, where one-dimensional and three-dimensional (1D-3D) calculations are coupled, to predict the surge boundary of centrifugal compressors. To validate this method, a high-speed centrifugal compressor is studied both by the proposed 1D-3D coupled method and experimentally. The results show the differences between predicted and experimentally determined stable flow range are lower than 5% until the Mach number of blade outlet tip tangential velocity reaches around 1.3. Besides, this method can correctly predict the instantaneous compressor performance during the surge cycle, so it can also be used to explore the surge mechanism and evaluate the blade dynamic force response in the future.

Copyright (c) 2018 by ASME
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