A Comparison between Measured and Computed Flow Fields in a Transonic Compressor Rotor

[+] Author and Article Information
P. W. McDonald, C. R. Bolt

Pratt and Whitney Aircraft, East Hartford, Conn. 06108

R. J. Dunker, H. B. Weyer

DFVLR, Institut fur Antriebstechnik, 5000 Cologne 90, West Germany

J. Eng. Power 102(4), 883-889 (Oct 01, 1980) (7 pages) doi:10.1115/1.3230354 History: Received December 03, 1979; Online September 28, 2009


The flow field within the rotor of a transonic axial compressor has been computed and compared to measurements obtained with an advanced laser velocimeter. The compressor was designed for a total pressure ratio of 1.51 at a relative tip Mach number of 1.4. The comparisons are made at 100 percent design speed (20,260 RPM) with pressure ratios corresponding to peak efficiency, near surge, and wide open discharge operating conditions. The computational procedure iterates between a blade-to-blade calculation and an intrablade through flow calculation. Calculated Mach number contours, surface pressure distributions, and exit total pressure profiles are in agreement with the experimental data demonstrating the usefulness of quasi three-dimensional calculations in compressor design.

Copyright © 1980 by ASME
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