The Development of a Second-Generation of Controlled Diffusion Airfoils for Multistage Compressors PUBLIC ACCESS

[+] Author Affiliations
R. F. Behlke

Pratt & Whitney, United Technologies Corporation, East Hartford, CT

Paper No. 85-IGT-9, pp. V001T02A003; 11 pages
  • ASME 1985 Beijing International Gas Turbine Symposium and Exposition
  • Volume 1: Aircraft Engine; Turbomachinery
  • Beijing, People’s Republic of China, September 1–7, 1985
  • Conference Sponsors: International Gas Turbine Institute
  • ISBN: 978-0-7918-7942-9
  • Copyright © 1985 by ASME


The evolution of Controlled Diffusion Airfoils is traced from inception of the theoretical design model to demonstration of significant performance gains at engine operating conditions in a multistage compressor rig. The proven aerodynamic benefits and versatility of first-generation Controlled Diffusion Airfoil blade elements are extended to the endwall flow region using an Integrated Core/Endwall Vortex design model to produce a new full span optimized second-generation Controlled Diffusion design. Highlighted are the essential roles of extensive cascade, low speed, large scale and high Mach number compressor rig testing in developing and substantiating the second generation Controlled Diffusion technology resulting in a 1.5% increase in efficiency and 30% increase in surge-free operation relative to first-generation Controlled Diffusion Airfoils.

Copyright © 1985 by ASME
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