Endwall Effects at Two Tip Clearances in a Multistage Axial Flow Compressor With Controlled Diffusion Blading

[+] Author and Article Information
M. A. Howard, J. P. Barton, K. F. Young

Rolls-Royce plc, Derby, United Kingdom

P. C. Ivey

School of Mechanical Engineering, Cranfield Institute of Technology, Bedford, United Kingdom

J. Turbomach 116(4), 635-645 (Oct 01, 1994) (11 pages) doi:10.1115/1.2929454 History: Received March 10, 1993; Online June 09, 2008


Effects of tip clearance, secondary flow, skew, and corner stall on the performance of a multistage compressor with controlled diffusion blading have been studied experimentally. Measurements between 1 and 99 percent annulus height were carried out in both the first and the third stages of a four-stage low-speed compressor with repeating-stage blading. Measurements were obtained at a datum rotor tip clearance and at a more aerodynamically desirable lower clearance. The consequences of the modified rotor tip clearance on both rotor and stator performance are examined in terms of loss coefficient and gas exit angle. Stator losses close to the casing are found to increase significantly when the clearance of an upstream rotor is increased. These increased stator losses cause 30 percent of the stage efficiency reduction that arises with increased rotor tip clearance. The deviation angles due to tip clearance from the multistage measurements are found to be similar to data from single-stage machines with conventional blading, which suggests that the unsteady flow phenomena associated with the multistage environment do not dominate the physics of the flow.

Copyright © 1994 by The American Society of Mechanical Engineers
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