Design Point Variation of Three-Dimensional Loss and Deviation for Axial Compressor Middle Stages

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

Flow Application Research, Fremont, CA 94539

G. K. Serovy

Iowa State University, Mechanical Engineering Department, Ames, IA 50011

D. M. Sandercock

NASA-Lewis Research Center, Cleveland, OH 44135

J. Turbomach 110(4), 426-433 (Oct 01, 1988) (8 pages) doi:10.1115/1.3262215 History: Received September 15, 1987; Online November 09, 2009


Three-dimensional spanwise pressure loss and flow angle deviation variations have been deduced from NASA, university, and industrial sources from middle-stage research compressors operating near design point. These variations are taken as the difference above or below that predicted by blade element theory at any spanwise location. It was observed that the magnitude of the three-dimensional loss and deviation in the endwall regions is affected by hub and casing boundary layer thickness, camber, solidity, and blade channel aspect ratio for stators and rotor hubs. Rotor tip variations were found to depend on casing boundary layer thickness and tip clearance. Simple design point loss models derived from these data can aid in the design of axial compressor middle stages.

Copyright © 1988 by ASME
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