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research-article

Redesign of a Compressor Stage for a High-Performance Electric Supercharger in a Heavily Downsized Engine

[+] Author and Article Information
Peng Wang

Advanced Design Technology Dilke House 1 Malet Street, London, WC1E 7JN United Kingdom
p.wang@adtechnology.co.uk

Mehrdad Zangeneh

Department of Mechanical Engineering University College London Torrington Place, London, WC1E 7JE United Kingdom
m.zangeneh@ucl.ac.uk

Bryn Richards

Aeristech Unit G,Princes Drive Industrial Estate Coventry Road, Warwickshire, CV8 2FD United Kingdom
bryn.richards@aeristech.co.uk

Kevin Gray

Aeristech Unit G,Princes Drive Industrial Estate Coventry Road, Warwickshire, CV8 2FD United Kingdom
kevin.gray@aeristech.co.uk

James Tran

Aeristech Unit G,Princes Drive Industrial Estate Coventry Road, Warwickshire, CV8 2FD United Kingdom
james.tran@aeristech.co.uk

Asuquo Andah

Aeristech Unit G,Princes Drive Industrial Estate Coventry Road, Warwickshire, CV8 2FD United Kingdom
asuquo.andah@aeristech.co.uk

1Corresponding author.

ASME doi:10.1115/1.4038021 History: Received July 16, 2017; Revised August 15, 2017

Abstract

Engine downsizing is a modern solution for the reduction of CO2 emissions from internal combustion engines. This technology has been gaining increasing attention from industry. In order to enable a downsized engine to operate properly at low speed conditions, it is essential to have a compressor stage with very good surge margin. The variable inlet guide vanes are a solution to this problem. By adjusting the setting angles of VIGVs, it is possible to shift the compressor map towards the smaller flow rates. However, this would also undermine the stage efficiency, require extra space for installing the IGVs, and add costs. The best solution is therefore to improve the design of impeller blade itself to attain high aerodynamic performances and wide operating ranges. This paper reports a recent study of using inverse design method for the redesign of a compressor stage used in an electric supercharger. The main requirements were to substantially increase the stable operating range of the compressor in order to meet the demands of the downsized engine. The 3D inverse design method was used to optimize the impeller geometry and achieve higher efficiency and stable operating range. The predicted performance map shows great advantages when compared with the existing design. To validate the CFD results, this new compressor stage has also been prototyped and tested. It will be shown that the CFD predictions have very good agreement with experiments and the redesigned compressor stage has improved the pressure ratio, aerodynamic efficiency, choke and surge margins considerably.

Copyright (c) 2017 by ASME
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