Aerodynamic Design and Performance of Five-Stage Transonic Axial-Flow Compressor

[+] Author and Article Information
Karl Kovach

Large Jet Engine Department, General Electric Company, Cincinnati, Ohio

D. M. Sandercock

Lewis Research Center, National Aeronautics and Space Administration, Cleveland, Ohio

J. Eng. Power 83(3), 303-320 (Jul 01, 1961) (18 pages) doi:10.1115/1.3673192 History: Received September 02, 1960; Online January 10, 2012


A five-stage axial-flow compressor with all rotors operating with transonic relative inlet Mach numbers was designed as a research vehicle at the Lewis Research Center in 1952. The compressor was designed and tested as a component of a turbojet engine. This paper summarizes the research work done on this compressor including the aerodynamic design and detailed performance characteristics.

Copyright © 1961 by ASME
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