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A First-Principles Based Methodology for Design of Axial Compressor Configurations

[+] Author Affiliations
Vishwas Iyengar, Lakshmi N. Sankar, Russ Denney

Georgia Institute of Technology, Atlanta, GA

Paper No. GT2007-27513, pp. 1301-1312; 12 pages
doi:10.1115/GT2007-27513
From:
  • ASME Turbo Expo 2007: Power for Land, Sea, and Air
  • Volume 6: Turbo Expo 2007, Parts A and B
  • Montreal, Canada, May 14–17, 2007
  • Conference Sponsors: International Gas Turbine Institute
  • ISBN: 0-7918-4795-0 | eISBN: 0-7918-3796-3
  • Copyright © 2007 by ASME

abstract

A multi-objective technique for designing single stage compressors is described. The blade geometry is defined as a function of known parametric equations, and the coefficient multipliers are viewed as design variables. A design of experiment approach is used to reduce the large combinations of design variables into a smaller subset. A response surface method is used to approximate the performance (total pressure rise, and adiabatic efficiency) as a function of design variables, and an optimum configuration is determined. This method has been applied to a rotor-stator combination similar to NASA Stage 35 with encouraging results.

Copyright © 2007 by ASME
Topics: Compressors , Design

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