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Optimization of Compressor Vane and Bleed Settings PUBLIC ACCESS

[+] Author Affiliations
J. E. Garberoglio, J. O. Song, W. L. Boudreaux

Pratt & Whitney Aircraft Group, West Palm Beach, FL

Paper No. 82-GT-81, pp. V001T01A034; 9 pages
doi:10.1115/82-GT-81
From:
  • ASME 1982 International Gas Turbine Conference and Exhibit
  • Volume 1: Turbomachinery
  • London, England, April 18–22, 1982
  • Conference Sponsors: International Gas Turbine Institute
  • ISBN: 978-0-7918-7956-6
  • Copyright © 1982 by ASME

abstract

Optimization of vane and bleed settings in a multistage axial compressor undergoing development is currently a difficult, time consuming, and very expensive process. The current technique usually consists of a detailed manual review of the internal aerodynamics after the baseline tests have been completed. If performance goals have not been met, the designers must estimate how vane and/or bleed settings might be changed to advantage and additional tests carried out until goals are met or time and budget are exhausted. The application of available test facility computer capacity to guide or possibly control the search for optimum compressor performance can ease this burden. This paper presents a numerical search optimization method for guiding the optimization of vane and bleed settings. The main element of the computer program is the COPES/CONMIN approximate optimization algorithm which has been programmed to permit optimization of four variable vane rows and one bleed. Calculations are presented to demonstrate the accuracy that can be achieved and the potential reduction in the number of data points and test time. Measurements on a three-stage, four-variable-vane compressor are presented to demonstrate the feasibility of using the software in conjunction with experimental tests.

Copyright © 1982 by ASME
This article is only available in the PDF format.

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