A Simplification Method for Computational Model of Cooling Losses from Turbine Vane
In this paper,numerical investigations were conducted on a high heat load blade of a gas turbine with film cooling injections by using CFD software ANSYS CFX.Two different simplification methods for computational model with single row of film holes were proposed for different situations,which could effectively simplify the model structure and save computational costs.This methodology could be applied on the numerical simulations of the straight blade with film cooling on vane surfaces.Additionally,a generation method of structured grid with multiple blocks was provided in this paper.
film coolingsimplification of computational modelstructured grid with multiple blocks
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