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Similarity Transformations for Compressor Blading PUBLIC ACCESS

[+] Author Affiliations
N. G. Zhu, L. Xu, M. Z. Chen

Beijing University of Aeronautics and Astronautics, Beijing, China

Paper No. 91-GT-123, pp. V001T01A048; 8 pages
doi:10.1115/91-GT-123
From:
  • ASME 1991 International Gas Turbine and Aeroengine Congress and Exposition
  • Volume 1: Turbomachinery
  • Orlando, Florida, USA, June 3–6, 1991
  • Conference Sponsors: International Gas Turbine Institute
  • ISBN: 978-0-7918-7898-9
  • Copyright © 1991 by ASME

abstract

Improving the performance of high speed axial compressors through low speed model compressor testing has proved to be economical and effective (Wisler, 1984). The key to this technique is to design low speed blade profiles which are aerodynamically similar to their high speed counterparts. The conventional aerodynamic similarity transformation involves the small disturbance potential flow assumption therefore its application is severely limited and generally not used in practical design. In this paper, a set of higher order transformation rules are presented which can accommodate large disturbances at transonic speed and are therefore applicable to similar transformations between the high speed HP compressor and its low speed model. Local linearization is used in the non–linear equations and the transformation is obtained in an iterative process. The transformation gives the global blading parameters such as camber, incidence and solidity as well as the blade profile. Both numerical and experimental validations of the transformation show that the non–linear similarity transformations do retain satisfactory accuracy for highly loaded blades up to low transonic speeds. Further improvement can be made by only slightly modifing profiles numerically without altering the global similarity parameters.

Copyright © 1991 by ASME
Topics: Compressors
This article is only available in the PDF format.

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