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CFD Modeling of a Gas Turbine Combustor From Compressor Exit to Turbine Inlet PUBLIC ACCESS

[+] Author Affiliations
D. Scott Crocker, Dan Nickolaus, Clifford E. Smith

CFD Research Corporation, Huntsville, AL

Paper No. 98-GT-184, pp. V003T06A007; 8 pages
doi:10.1115/98-GT-184
From:
  • ASME 1998 International Gas Turbine and Aeroengine Congress and Exhibition
  • Volume 3: Coal, Biomass and Alternative Fuels; Combustion and Fuels; Oil and Gas Applications; Cycle Innovations
  • Stockholm, Sweden, June 2–5, 1998
  • Conference Sponsors: International Gas Turbine Institute
  • ISBN: 978-0-7918-7864-4
  • Copyright © 1998 by ASME

abstract

Gas turbine combustor CFD modeling has become an important combustor design tool in the past few years, but CFD models are generally limited to the flow field inside the combustor liner or the diffuser/combustor annulus region. Although strongly coupled in reality, the two regions have rarely been coupled in CFD modeling. A CFD calculation for a full model combustor from compressor diffuser exit to turbine inlet is described. The coupled model accomplishes two main objectives: 1) implicit description of flow splits and flow conditions for openings into the combustor liner, and 2) prediction of liner wall temperatures. Conjugate heat transfer with nonluminous gas radiation (appropriate for lean, low emission combustors) is utilized to predict wall temperatures compared to the conventional approach of predicting only near wall gas temperatures. Remaining difficult issues such as generating the grid, modeling swirler vane passages, and modeling effusion cooling are also discussed.

Copyright © 1998 by ASME
This article is only available in the PDF format.

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