Development of a Transonic Front Stage of an Axial Flow Compressor for Industrial Gas Turbines

[+] Author and Article Information
Y. Katoh, H. Ishii, Y. Tsuda, M. Yanagida

Mechanical Engineering Research Laboratory, Hitachi, Ltd., Hitachi, Ibaraki, Japan

Y. Kashiwabara

Department of Mechanical Systems Engineering, Kanagawa Institute of Technology, Atsugi, Kanagawa, Japan

J. Turbomach 116(4), 605-611 (Oct 01, 1994) (7 pages) doi:10.1115/1.2929450 History: Received March 12, 1993; Online June 09, 2008


This paper describes the aerodynamic blade design of a highly loaded three-stage compressor, which is a model compressor for the front stage of an industrial gas turbine. Test results are presented that confirm design performance. Some surge and rotating stall measurement results are also discussed. The first stator blade in this test compressor operates in the high subsonic range at the inlet. To reduce the pressure loss due to blade surface shock waves, a shock-free airfoil is designed to replace the first stator blade in an NACA-65 airfoil in a three-stage compressor. Comparison of the performance of both blades shows that the shock-free airfoil blade reduces pressure loss. This paper also presents some experimental results for MCA (multicircular arc) airfoils, which are used for first rotor blades.

Copyright © 1994 by The American Society of Mechanical Engineers
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