LES of Reacting Flows in an Industrial Gas Turbine Combustor
Journal of Propulsion and Power
American Institute of Aeronautics and Astronautics
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Langella, I., Chen, Z. X., Swaminathan, S., & Sadasivuni, S. K. LES of Reacting Flows in an Industrial Gas Turbine Combustor. Journal of Propulsion and Power https://doi.org/10.17863/CAM.22540
The turbulent reacting flow in an industrial gas turbine combustor operating at 3 bar is computed using LES paradigm. The subgrid scale (SGS) combustion is modelled using a collection of unstrained premixed flamelets including mixture stratification. The non-premixed combustion mode is also included using a simple closure involving the scalar dissipation rate of the mixture fraction. A close attention is paid to maintain physical consistencies among sub-closure models for combustion and these consisten- cies are discussed on a physical basis. The importance of non-premixed mode and SGS mixture fraction fluctuations are investigated systematically. The results show that the SGS mixture fraction variance plays an important role and comparisons to measure- ments improve when contributions from the premixed and non-premixed modes are included. These numerical results and observations are discussed on a physical basis along with potential avenues for further improvements.
This record's DOI: https://doi.org/10.17863/CAM.22540
This record's URL: https://www.repository.cam.ac.uk/handle/1810/275350