Application of Numerical Models for Predictions of Turbine Engine Combustor Performance FREE

[+] Author Affiliations
D. L. Burrus

GE Aircraft Engines, Cincinnati, OH

Paper No. 89-GT-251, pp. V003T06A005; 11 pages
  • 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


Rapid advances in available computer technology in the past ten years coupled with the ever increasing costs associated with gas turbine combustor development testing led to considerable interest in the development of sophisticated numerical methods for the design and analysis of turbine engine combustors. The development and refinement of these methods has been taking place at GE Aircraft Engines since 1980 as part of an ongoing research and development project. Efforts associated with this project have achieved considerable progress to date, including the development of 2D/axisymmetric and full 3D versions of an improved elliptic numerical model (CONCERT), suitable for application to combustor related flow problems. The application of CONCERT to typical combustor performance problems has demonstrated its capabilities to provide useful and accurate design information resulting in less dependence on component testing. This has resulted in engineering productivity improvement and reduced costs associated with combustor performance development.

Copyright © 1989 by ASME
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