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Integrated RANS-LES Computations of Turbomachinery Components: Generic Compressor/DiffuserThe goal of the current study is to apply the coupled RANS-LES approach to a compressor-diffuser geometry of a gas turbine. This flow configuration is important, since the outflow of the compressor alters the flow field in the subsequent diffuser. A detailed knowledge of the flow field in this section allows to optimize the difuser design in order to to achieve a decrease of pressure loss. Here, the NASA stage 35 compressor is coupled with a generic diffuser in order to assess the integrated RANS-LES approach.
Document ID
20040031726
Acquisition Source
Ames Research Center
Document Type
Other
Authors
Schlueter, J. U. (Stanford Univ. Stanford, CA, United States)
Wu, X. (Stanford Univ. Stanford, CA, United States)
Kim, S. (Stanford Univ. Stanford, CA, United States)
Alonso, J. J. (Stanford Univ. Stanford, CA, United States)
Pitsch, H. (Stanford Univ. Stanford, CA, United States)
Date Acquired
September 7, 2013
Publication Date
January 1, 2003
Publication Information
Publication: Center for Turbulence Research Annual Research Briefs 2003
Subject Category
Fluid Mechanics And Thermodynamics
Funding Number(s)
CONTRACT_GRANT: NCC2-1371
Distribution Limits
Public
Copyright
Work of the US Gov. Public Use Permitted.

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