Modeling the 3-D Flow Effects on Deviation Angle for Axial Compressor Middle Stages

[+] Author and Article Information
W. B. Roberts

Flow Application Research, Fremont, CA

G. K. Serovy

Mechanical Engineering Department, Iowa State University, Ames, IA

D. M. Sandercock

National Aeronautics and Space Administration, Lewis Research Center, Cleveland, OH

J. Eng. Gas Turbines Power 108(1), 131-137 (Jan 01, 1986) (7 pages) doi:10.1115/1.3239859 History: Received January 07, 1985; Online October 15, 2009


A model of the spanwise variation of the 3-D flow effects on deviation is proposed for middle-stage rotors and stators. This variation is taken as the difference above or below that predicted by blade element theory at any spanwise location. It was found that the stator variation is strongly affected by the end-wall boundary-layer thickness as well as camber, solidity, and blade channel aspect ratio. Rotor variation was found to depend on end-wall boundary layer thickness and tip clearance normalized by blade span. If these parameters are known or can be calculated, the models provide a reasonable approximation to the spanwise variation of deviation for middle compressor stages operating at low to high subsonic inlet Mach numbers.

Copyright © 1986 by ASME
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