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RESEARCH PAPERS

Endwall Blockage in Axial Compressors

[+] Author and Article Information
S. A. Khalid

Allison Advanced Development Co., Indianapolis, IN 46206-7162

A. S. Khalsa

Khalsa International Industries and Trades, Española, NM 87532

I. A. Waitz, C. S. Tan, E. M. Greitzer

Gas Turbine Laboratory, Massachusetts Institute of Technology, Cambridge, MA 02139

N. A. Cumpsty

Whittle Laboratory, Cambridge University, Cambridge, United Kingdom

J. J. Adamczyk

NASA Lewis Research Center, Cleveland, OH 44135

F. E. Marble

California Institute of Technology, Pasadena, CA 91125

J. Turbomach 121(3), 499-509 (Jul 01, 1999) (11 pages) doi:10.1115/1.2841344 History: Received February 01, 1998; Online January 29, 2008

Abstract

This paper presents a new methodology for quantifying compressor endwall blockage and an approach, using this quantification, for defining the links between design parameters, flow conditions, and the growth of blockage due to tip clearance flow. Numerical simulations, measurements in a low-speed compressor, and measurements in a wind tunnel designed to simulate a compressor clearance flow are used to assess the approach. The analysis thus developed allows predictions of endwall blockage associated with variations in tip clearance, blade stagger angle, inlet boundary layer thickness, loading level, loading profile, solidity, and clearance jet total pressure. The estimates provided by this simplified method capture the trends in blockage with changes in design parameters to within 10 percent. More importantly, however, the method provides physical insight into, and thus guidance for control of, the flow features and phenomena responsible for compressor endwall blockage generation.

Copyright © 1999 by The American Society of Mechanical Engineers
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