关键词: 非对称扇形孔, 航空宇航推进系统, 气膜冷却, 扇形孔, 涡轮叶片, 变转速控制, 复合控制, 能效, 电液动力源

Abstract: A numerical study is conducted to investigate the effect of the lateral diffusion angle of fan-shaped holes on the blade film cooling effectiveness at the suction and pressure surfaces. The baseline fan geometry has a 20° lateral diffusion and 10° laidback expansion. Film cooling effectiveness for asymmetrical fan-shaped holes is studied at different blowing ratios (from 0.44 to 2.67). Under the same total lateral diffusion angle of fan-shaped holes, the coolant jet penetration from the asymmetrical fan-shaped holes is equal to that from baseline fan geometry, but the film coverage in lateral direction is improved a little, which is obvious at the higher blowing ratio. And the asymmetrical fan-shaped holes are suitable to be applied to the pressure surface of turbine blade

Key words: Aerospace propulsion system, Asymmetrical fan-shaped holes, Fan-shaped holes, Film cooling, Turbine blade, energy saving, pressure and flow compound control, speed variable control, electro-hydraulic power source