Blockage Development in a Transonic, Axial Compressor Rotor

[+] Author and Article Information
K. L. Suder

NASA-Lewis Research Center, Cleveland, OH 44135

J. Turbomach 120(3), 465-476 (Jul 01, 1998) (12 pages) doi:10.1115/1.2841741 History: Received February 01, 1997; Online January 29, 2008


A detailed experimental investigation to understand and quantify the development of blockage in the flow field of a transonic, axial flow compressor rotor (NASA Rotor 37) has been undertaken. Detailed laser anemometer measurements were acquired upstream, within, and downstream of a transonic, axial compressor rotor operating at 100, 85, 80, and 60 percent of design speed, which provided inlet relative Mach numbers at the blade tip of 1.48, 1.26, 1.18, and 0.89, respectively. The impact of the shock on the blockage development, pertaining to both the shock/boundary layer interactions and the shock/tip clearance flow interactions, is discussed. The results indicate that for this rotor the blockage in the endwall region is 2–3 times that of the core flow region, and the blockage in the core flow region more than doubles when the shock strength is sufficient to separate the suction surface boundary layer.

Copyright © 1998 by The American Society of Mechanical Engineers
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