A Study on Design and Test for Combustor and Fuel Nozzles of a Small Aircraft Gas Turbine PUBLIC ACCESS

[+] Author Affiliations
C. D. Kong, S. K. Kim

Chosun University, Kwangju, Republic of Korea

Paper No. 97-AA-015, pp. V001T05A005; 10 pages
  • ASME 1997 Turbo Asia Conference
  • ASME 1997 Turbo Asia Conference
  • Singapore, September 30–October 2, 1997
  • Conference Sponsors: International Gas Turbine Institute
  • ISBN: 978-0-7918-7867-5
  • Copyright © 1997 by ASME


A combustor and a fuel nozzle for a small aircraft gas turbine were designed and appropriateness for design requirements were evaluated and confirmed through the cold and hot test. For the purpose of studying the flame stability of a pilot atomizer under ignition, firing tests were carried out at the various fuel supply pressures. As the results of the experiment and design revision, the optimal combination of the fuel nozzle which is suitable to the design requirement was obtained without the fuel splash phenomena and unstable flame. The combustor was designed and evaluated with detailed investigations and experiments for design requirements. As the results of the hot test, it was confirmed that the combustor in this study had proper profile and pattern factors, flammability limit, total pressure loss and combustor efficiency within design requirements.

Copyright © 1997 by ASME
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