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RESEARCH PAPERS

Effect of Area Ratio on the Performance of a 5.5:1 Pressure Ratio Centrifugal Impeller

[+] Author and Article Information
L. F. Schumann, D. A. Clark

Propulsion Directorate, U.S. Army Aviation Research and Technology Activity—AVSCOM, Lewis Research Center, Cleveland, OH 44135

J. R. Wood

NASA Lewis Research Center, Cleveland, OH 44135

J. Turbomach 109(1), 10-19 (Jan 01, 1987) (10 pages) doi:10.1115/1.3262055 History: Received March 07, 1986; Online November 09, 2009

Abstract

A centrifugal impeller which was initially designed for a pressure ratio of approximately 5.5 and a mass flow rate of 0.959 kg/s was tested with a vaneless diffuser for a range of design point impeller area ratios from 2.322 to 2.945. The impeller area ratio was changed by successively cutting back the impeller exit axial width from an initial value of 7.57 mm to a final value of 5.97 mm. In all, four separate area ratios were tested. For each area ratio a series of impeller exit axial clearances was also tested. Test results are based on impeller exit surveys of total pressure, total temperature, and flow angle at a radius 1.115 times the impeller exit radius. Results of the tests at design speed, peak efficiency, and an exit tip clearance of 8 percent of exit blade height show that the impeller equivalent pressure recovery coefficient peaked at a design point area ratio of approximately 2.748 while the impeller aerodynamic efficiency peaked at a lower value of area ratio of approximately 2.55. The variation of impeller efficiency with clearance showed expected trends with a loss of approximately 0.4 points in impeller efficiency for each percent increase in exit axial tip clearance for all impellers tested. The data also indicated that the impeller would probably separate at design area ratios greater than 2.748. An analysis was performed with a quasi-three-dimensional inviscid computer code which confirmed that a minimum velocity ratio was attained near this area ratio thus indicating separation. These data can be used to verify impeller flow models which attempt to account for very high diffusion and possible separation.

Copyright © 1987 by ASME
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