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Research and Development of Turbo Jet Combustor on HST Programme in Japan PUBLIC ACCESS

[+] Author Affiliations
T. Kuyama, Y. Enzaki, M. Kawano, M. Kobayashi

Kawasaki Heavy Industries Limited, Kobe, Japan

Paper No. 93-GT-400, pp. V03CT17A061; 8 pages
doi:10.1115/93-GT-400
From:
  • ASME 1993 International Gas Turbine and Aeroengine Congress and Exposition
  • Volume 3C: General
  • Cincinnati, Ohio, USA, May 24–27, 1993
  • Conference Sponsors: International Gas Turbine Institute
  • ISBN: 978-0-7918-7892-7
  • Copyright © 1993 by ASME

abstract

The research and development of a turbo jet combustor for a Mach 3 class supersonic transport is underway, as well as the other components of the HST programme in JAPAN. This research and development aims finally at achieving a combustor exit temperature of 1973K while maintaining low NOx levels, high durability, and good exit temperature distribution.

This paper describes the interim status of the combustor research and development, in particular, the liner cooling system and exit temperature distribution control technique.

Copyright © 1993 by ASME
This article is only available in the PDF format.

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