NASA NTRS · 20040031726
Integrated RANS-LES Computations of Turbomachinery Components: Generic Compressor/Diffuser
Abstract
The 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.
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Schlueter, J. U., Wu, X., Kim, S., Alonso, J. J., Pitsch, H.. 2003-01-01. Integrated RANS-LES Computations of Turbomachinery Components: Generic Compressor/Diffuser. https://ntrs.nasa.gov/citations/20040031726
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