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Experimental Investigation of a Cooling System Entrance for an Annular Gas Turbine Combustion Chamber FREE

[+] Author Affiliations
Lars O. Lindqvist, Ulf E. Nilsson, Jonas N. Hylén

ABB STAL, Finspong, Sweden

Paper No. 97-GT-477, pp. V002T06A060; 9 pages
doi:10.1115/97-GT-477
From:
  • ASME 1997 International Gas Turbine and Aeroengine Congress and Exhibition
  • Volume 2: Coal, Biomass and Alternative Fuels; Combustion and Fuels; Oil and Gas Applications; Cycle Innovations
  • Orlando, Florida, USA, June 2–5, 1997
  • Conference Sponsors: International Gas Turbine Institute
  • ISBN: 978-0-7918-7869-9
  • Copyright © 1997 by ASME

abstract

A cooling entrance region for a modern annular combustor has been successfully tested. Because of high heat load at the entrance part of the liner, a good design is very important. The design presented here offers ultra-low dilution, robustness and high performance. The cooling system includes convective, film and impingement techniques, which were experimentally investigated in a plastic (perspex) model of a full scale 60° sector of a simplified combustor design. The importance of a high performance entrance is obvious. It generates low pressure drop, better combustion (circumferential even flow for the liner cooling) and it gives lower flame temperature (maximizes the air in the flame). Guidelines for the design of such an entrance are presented in this paper.

Copyright © 1997 by ASME
This article is only available in the PDF format.

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