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Improvements to the Performance of a Prototype Pulse, Pressure Gain, Gas-Turbine Combustor FREE

[+] Author Affiliations
J. A. C. Kentfield, L. C. V. Fernandes

University of Calgary, Calgary, AB, Canada

Paper No. 89-GT-277, pp. V003T06A020; 7 pages
doi:10.1115/89-GT-277
From:
  • ASME 1989 International Gas Turbine and Aeroengine Congress and Exposition
  • Volume 3: Coal, Biomass and Alternative Fuels; Combustion and Fuels; Oil and Gas Applications
  • Toronto, Ontario, Canada, June 4–8, 1989
  • Conference Sponsors: International Gas Turbine Institute
  • ISBN: 978-0-7918-7915-3
  • Copyright © 1989 by ASME

abstract

A description is given of a simple, prototype, pulse, pressure-gain, combustor for a gas turbine. The work reported was targeted at alleviating problems previously observed with the prototype combustor. These were related to irreversibilities, causing a performance deficiency, in the secondary flow passage. The work consisted of investigating experimentally the effect of tuning the secondary-flow path-length, adding a flow restrictor at the combining-cone entry station and redesigning the combining-cone itself. The overall result was to eradicate the previously noted performance deficiency thereby increasing the maximum pressure-gain obtained in the gas turbine from 1.6% to 4.0% of the compressor absolute delivery pressure.

Copyright © 1989 by ASME
This article is only available in the PDF format.

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