비등각 격자를 이용한 막냉각 해석

Abstract

The turbine blade experiences a harsh thermal environment. To maintain the integrity of the blades, improved coolant design are required, film cooling being one of them. The CFD tool is used for designing the film cooled blade. However generating meshes based on hexahedral elements, which are often associated with accuracy solutions, is very time consuming task due to complexity of geometry. The objective of this paper is to better establish the effects of mesh generation techniques on film cooling. In order to achieve this objective, non-conformal mesh has been considered using discrete jet on a flat plate film cooling. Mesh density and interface location of non-conformal mesh influence on adiabatic film cooling effectiveness were presented. The Numerical results were compared to experimental data for validation.