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research-article

Centrifugal compressor performance improvements through compressor splitter location

[+] Author and Article Information
Cheng Xu

Department of Mechanical Engineering, University of Wisconsin, Milwaukee, WI 53210, USA
xuc2@asme.org

Ryo Amano

Department of Mechanical Engineering, University of Wisconsin, Milwaukee, WI 53210, USA
amano@uwm.edu

1Corresponding author.

ASME doi:10.1115/1.4037813 History: Received June 10, 2017; Revised August 27, 2017

Abstract

In centrifugal compressor impellers, the splitter blades are very common to use. In this study, a low flow single-stage centrifugal compressor with a vaneless diffuser was used to investigate the location effects of the impeller splitter between two main blades. It is demonstrated that the splitter location provided an opportunity to improve the compressor performance and reduce the operational cost. The splitter location optimizations were performed numerically, and the optimal splitter location was identified. A prototype was built for the impeller with optimal splitter location. The performance tests were performed, and test results are compared with numerical analysis. The studies indicated that splitter locations have impacts to the compressor stage performances. The optimization for the splitter location can enhance the centrifugal compressor performance. The studies showed that the traditional splitter located at the middle of the two main blades is not the optimal location for aerodynamic performance. The splitter location optimization provided the opportunity to improve the centrifugal compressor performance further.

Copyright (c) 2017 by ASME
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