The Effect Of The Orifices Shape On The Cooling Film On Gas Turbine Blade (3d Numerical Study)

Résumé: EN Gas turbines are widely used in industrial applications, terrestrial power production, and aviation propulsion. Technological advances in turbine cooling are key to increasing modern gas turbines power output and thermal efficiency. To remove heat transferred from the outside surface, coolant is pumped through multiple serpentine tunnels with rib enhancements to internally cool the gas turbine blades. By forcing slightly cooler air from the internal coolant passages out of the blade surface, membrane cooling, an external cooling technique for turbine blades, creates a barrier between the flow of the hot gas stream and the blade surface. The present study numerically investigated the effects of hole configuration and inclination angle on film cooling effectiveness, particle deposition at various blowing ratios, and prediction of multiple parameters using CFD. The results show that, among the three-hole shapes (Cylindrique, Rectangular, Crescent), At the blowing ratio of M=2, the crescent hole shows the best cooling performance. For the effect of inclination angle on cooling performance, the film cooling effectiveness of the three different hole configurations at various inclination angles (30◦,60°), the angle of 30° accorded with the best film cooling effect.

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