Large Eddy Simulation on compound angle film cooling of turbine blades

Abstract

Large Eddy Simulation (LES) was performed to investigate the flow structures and the development process of vortices in different sections of a stationary gas turbine at M=1.5, while the jet hole of the leading edge has compound angle. The results show that the jet in a cross-flow is a highly complex turbulent flow due to the action of many structures in the field, including the jet shear-layer vortices, the system of horseshoe vortices, the counter-rotating vortex pair, and the wake vortices. The cooling effectiveness is better on the suction side and on the pressure side with laying compound angles film-cooling holes. The vortices in the centreplane are shed off to form new vortices periodically with period of 0.04s. The generation of CVP on the pressure side is earlier than that on the suction side and the effect of CVP on the pressure side is stronger than that on the suction side.

The Use of Compound Cooling Holes for Film Cooling at the End Wall of Combustor Simulator

“…Zhang et al [16] considered computational results of flow behavior in different parts of a stationary gas turbine vane at blowing ratio of 1.50 and compound holes application at the leading edge by using LES model. The results declared that the suitable arrangement of compound angle holes produced the best cooling condition in both pressure and suction sides of turbine vane.…”