By using an integrated model with disc cavity and turbine blade,the endwall film cooling effectiveness was investigated numerically by using the shear stress transfer(SST)model to solve the Reynolds-averaged Naiver-Stokes(RANS)equation.The rotational Reynolds number at the outlet of the disc cavity was 1.5 × 105.Carbon dioxide was chosen as the coolant to maintain the coolant-to-mainstream density ratio.The diffusion process of coolant was characterized by solving the turbulent transport equation.The effect of coolant inlet angle(-45°,0°,+45°)on the endwall film cooling effectiveness was investigated.It was found that the inlet angle of coolant had a significant impact on the endwall film cooling effectiveness,and the-45° inlet angle can significantly improve the endwall film cooling effectiveness at various coolant-to-mainstream mass flow rates.
gas turbine engineturbine bladeendwallleakage flowfilm cooling
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