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RESEARCH PAPERS

Development of Controlled Diffusion Airfoils for Multistage Compressor Application

[+] Author and Article Information
D. E. Hobbs, H. D. Weingold

Pratt & Whitney Aircraft, Engineering Division, United Technologies Corporation, East Hartford, Conn. 06108

J. Eng. Gas Turbines Power 106(2), 271-278 (Apr 01, 1984) (8 pages) doi:10.1115/1.3239559 History: Received January 04, 1983; Online October 15, 2009

Abstract

A series of Controlled Diffusion Airfoils has been developed for multistage compressor application. These airfoils are designed analytically to be shock-free at transonic Mach numbers and to avoid suction surface boundary layer separation for a range of inlet conditions necessary for stable compressor operation. They have demonstrated, in cascade testing, higher critical Mach numbers, higher incidence range, and higher loading capability than standard series airfoils designed for equivalent aerodynamic requirements. These airfoils have been shown, in single and multistage rig testing, to provide high efficiency, high loading capability, and ease of stage matching, leading to reduced development costs and improved surge margin. The Controlled Diffusion Airfoil profile shapes tend to have thicker leading and trailing edges than their standard series counterparts, which lead to improved compressor durability.

Copyright © 1984 by ASME
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