Development of a High-Pressure-Ratio Axial Flow Compressor for a Medium-Size Gas Turbine

[+] Author and Article Information
Y. Kashiwabara, Y. Matsuura, Y. Katoh, N. Hagiwara, T. Hattori

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

K. Tokunaga

Hitachi Works, Hitachi, Ltd., Hitachi, Ibaraki, Japan

J. Turbomach 108(2), 233-239 (Oct 01, 1986) (7 pages) doi:10.1115/1.3262042 History: Received January 17, 1986; Online November 09, 2009


In this paper, the development of a model 17-stage axial compressor (pressure ratio 14.7) for a medium-size gas turbine is described. The aerodynamic and mechanical design features of the compressor are presented. In advance of the full 17-stage test, the first three and nine stages were tested. Measured results confirm the design performance in the first stages of the 17-stage compressor. The details of the construction of the facilities, instrumentation and data acquisition system for the full 17-stage test are described. Test results for the 17-stage compressor are presented. The measured results are in good agreement with the predicted values.

Copyright © 1986 by ASME
Your Session has timed out. Please sign back in to continue.






Some tools below are only available to our subscribers or users with an online account.

Related Content

Customize your page view by dragging and repositioning the boxes below.

Topic Collections

Sorry! You do not have access to this content. For assistance or to subscribe, please contact us:

  • TELEPHONE: 1-800-843-2763 (Toll-free in the USA)
  • EMAIL: asmedigitalcollection@asme.org
Sign In