Integrated Simulations for Multi-Component Analysis of Gas Turbines:RANS Boundary Conditions

The aero-thermal computation of the flow path of an entire gas turbine engine can be performed using multiple flow solvers, each specialized to a component of the engine. Here, we present an approach to integrate a Large Eddy Simulation (LES) solver and a Reynolds Averaged Navier-Stokes (RANS) solver. Challenges arise, when the LES solver is based on a low-Mach number approximation and can not deliver all variables needed for a compressible RANS solver. This study investigates the choice of boundary conditions applied to the RANS interface. We propose the use of inlet/exit boundary conditions and investigate the effect on simple pipe geometries.

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