Evaluation of a High Hub/Tip Ratio Centrifugal Compressor

[+] Author and Article Information
F. G. Groh, G. M. Wood, R. S. Kulp

Pratt & Whitney Aircraft Division, United Aircraft Corp., East Hartford, Conn.

D. P. Kenny

Compressor Research, United Aircraft of Canada, Ltd., Ville Jacques Cartier, Canada

J. Basic Eng 92(3), 419-428 (Sep 01, 1970) (10 pages) doi:10.1115/1.3425017 History: Received July 28, 1969; Online October 27, 2010


A centrifugal compressor stage with an unusually high inlet hub/tip ratio of 0.87 was designed for a pressure ratio of 2.0 at a corrected mass flow of 2.45 lb per sec. The geometry was selected so that the centrifugal stage could replace several of the last stages of a multistage axial compressor. The stage was tested with two diffuser schemes. One diffuser consisted of a series of drilled conical pipes, whereas the other employed multirow vaned cascades. Sea level aerodynamic tests of the compressor stage with each diffuser showed a peak total-to-total efficiency at design speed of 83.8 percent for the pipe diffuser and 82.9 percent for the vaned cascade diffuser. Additional tests were conducted with a vaneless diffuser to determine effects of impeller discharge tip clearance and inlet prewhirl on impeller performance.

Copyright © 1970 by ASME
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