An Investigation of the Stability Enhancement of a Centrifugal Compressor Stage using a Porous Throat Diffuser

[+] Author and Article Information
Lee Galloway

Queen’s University Belfast Belfast, United Kingdom

Stephen W T Spence

Queen’s University Belfast Belfast, United Kingdom

Sung in Kim

Queen’s University Belfast Belfast, United Kingdom

Daniel Rusch

ABB Turbo Systems Ltd. Baden, Switzerland

Klemens Vogel

ABB Turbo Systems Ltd. Baden, Switzerland

Rene Hunziker

ABB Turbo Systems Ltd. Baden, Switzerland

1Corresponding author.

ASME doi:10.1115/1.4038181 History: Received September 12, 2017; Revised October 03, 2017


There have been many techniques employed to increase the stable operating range of centrifugal compressor stages. The literature demonstrates that there are various possibilities for adding special treatments to the nominal diffuser vane geometry, or including injection or bleed flows to modify the diffuser flow field in order to influence diffuser stability. One such treatment is the porous throat diffuser. Although the benefits of this technique have been proven in the existing literature, a comprehensive understanding of how this technique operates is not yet available. This paper uses experimental measurements from a high pressure ratio compressor stage to acquire a sound understanding of the flow features within the vaned diffuser which affect the stability of the overall compression system and investigate the stabilising mechanism of the porous throat diffuser. The non-uniform circumferential pressure imposed by the asymmetric volute is experimentally and numerically examined to understand if this provides a preferential location for stall inception in the diffuser. The following hypothesis is confirmed: linking of the diffuser throats via the side cavity equalizes the diffuser throat pressure, thus creating a more homogeneous circumferential pressure distribution, which delays stall inception to lower flow rates. The results of the porous throat diffuser configuration are compared to a standard vaned diffuser compressor stage in terms of overall compressor performance parameters, circumferential pressure non-uniformity at various locations through the compressor stage and diffuser sub-component analysis.

Copyright (c) 2017 by ASME
Your Session has timed out. Please sign back in to continue.






Some tools below are only available to our subscribers or users with an online account.

Related Content

Customize your page view by dragging and repositioning the boxes below.

Related Journal Articles
Related eBook Content
Topic Collections

Sorry! You do not have access to this content. For assistance or to subscribe, please contact us:

  • TELEPHONE: 1-800-843-2763 (Toll-free in the USA)
  • EMAIL: asmedigitalcollection@asme.org
Sign In