0
research-article

AERODYNAMIC OPTIMIZATION OF A TRANSONIC CENTRIFUGAL COMPRESSOR BY USING ARBITRARY BLADE SURFACES

[+] Author and Article Information
Alexander Hehn

Institute of Jet Propulsion and Turbomachinery, RWTH Aachen, Templergraben 55, 52062 Aachen, Germany
hehn@ist.rwth-aachen.de

Moritz Mosdzien

Institute of Jet Propulsion and Turbomachinery, RWTH Aachen, Templergraben 55, 52062 Aachen, Germany
mosdzien@ist.rwth-aachen.de

Daniel Grates

Institute of Jet Propulsion and Turbomachinery, RWTH Aachen, Templergraben 55, 52062 Aachen, Germany
grates@ist.rwth-aachen.de

Peter Jeschke

Institute of Jet Propulsion and Turbomachinery, RWTH Aachen, Templergraben 55, 52062 Aachen, Germany
jeschke@ist.rwth-aachen.de

1Corresponding author.

ASME doi:10.1115/1.4038908 History: Received November 18, 2017; Revised December 20, 2017

Abstract

A transonic centrifugal compressor was aerodynamically optimized by means of a numerical optimization process. The ob- jectives were to increase the isentropic efficiency and to reduce the acoustic signature by decreasing the amplitude of pre shock pressure waves at the inlet of the compressor. The optimization was performed at three operating points on the 100% speed line in order to maintain choke mass flow and surge margin. At the de- sign point, the specific work input was kept equal. The baseline impeller was designed by using ruled surfaces due to require- ments for flank milling. To investigate the benefits of arbitrary blade surfaces, the restrictions of ruled surfaces were abolished and fully 3D blade profiles allowed. In total therefore, 45 pa- rameters were varied during the optimization. The combined ge- ometric and aerodynamic analysis reveals that a forward swept leading edge and a concave suction side at the tip of the leading edge are effective design features for reducing the shock strength. Beyond that the blade shape of the optimized compressor creates a favorable impeller outlet flow, which is the main reason why the performance of the vaneless diffuser improves. In total a gain of 1.4%-points in isentropic total-to-static efficiency, evaluated by CFD at the exit plane of the vaneless diffuser, is achieved.

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

References

Figures

Tables

Errata

Discussions

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