The numerical prediction of the entire aero-thermal flow through an entire gas turbine is currently limited by its high computational costs. The approach presented here intends to use several specialized flow solvers based on the Reynolds-averaged Navier-Stokes equations (RANS) as well as Large Eddy Simulations (LES) running simultaneously and exchanging information at the interfaces. This study documents the development of the interface and proves its accuracy and efficiency on simple test-cases. Furthermore, its application to a turbo-machinery application is demonstrated.

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