高速条件下吸力面复合角孔气膜冷却特性

To investigate the film cooling characteristics of compound angle holes on turbine vane under high-speed conditions，a row of compound angle holes were set up on the suction surface of the turbine vane. The film cooling effectiveness and heat transfer coefficient ratio of the compound angle holes were measured. And the net gain of film cooling was measured by net heat flux reduction (NHFR). The effects of Reynolds number，blowing ratio and turbulence intensity on the film cooling effectiveness，heat transfer coefficient ratio and net heat flux reduction were analyzed. It was found that the film cooling effectiveness was affected by the Reynolds number，but when Reynolds number was larger than 6.4×10⁵，the film cooling effectiveness almost didn’t change with Reynolds number any more. When the turbulence intensity increased，the film cooling effectiveness decreased，making it more sensitive to the turbulence intensity at a low blowing ratio. The heat transfer coefficient ratio increased with the blowing ratio，but its sensitivity decreased under higher turbulence intensity. When the turbulence intensity increased，NHFR also increased. In general，at the blowing ratio is 0.8，the compound angle hole presents the best film cooling performance at a higher turbulence intensity.