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Experimental Replication of an Aeroengine Combustion Instability

[+] Author Affiliations
J. M. Cohen, J. R. Hibshman, W. Proscia, T. J. Rosfjord, B. E. Wake

United Technologies Research Center, East Hartford, CT

J. B. McVey

jbScienceS, Glastonbury, CT

J. Lovett, M. Ondas

Pratt & Whitney, West Palm Beach, FL

J. DeLaat, K. Breisacher

NASA Glenn Research Center at Lewis Field, Cleveland, OH

Paper No. 2000-GT-0093, pp. V002T02A013; 9 pages
doi:10.1115/2000-GT-0093
From:
  • ASME Turbo Expo 2000: Power for Land, Sea, and Air
  • Volume 2: Coal, Biomass and Alternative Fuels; Combustion and Fuels; Oil and Gas Applications; Cycle Innovations
  • Munich, Germany, May 8–11, 2000
  • Conference Sponsors: International Gas Turbine Institute
  • ISBN: 978-0-7918-7855-2
  • Copyright © 2000 by ASME

abstract

Combustion instabilities in gas turbine engines are most frequently encountered during the late phases of engine development, at which point they are difficult and expensive to fix. The ability to replicate an engine-traceable combustion instability in a laboratory-scale experiment offers the opportunity to economically diagnose the problem more completely (to determine the root cause), and to investigate solutions to the problem, such as active control. The development and validation of active combustion instability control requires that the causal dynamic processes be reproduced in experimental test facilities which can be used as a test bed for control system evaluation. This paper discusses the process through which a laboratory -scale experiment can be designed to replicate an instability observed in a developmental engine. The scaling process used physically-based analyses to preserve the relevant geometric, acoustic and thermo-fluid features, ensuring that results achieved in the single-nozzle experiment will be scaleable to the engine.

Copyright © 2000 by ASME
Topics: Combustion

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