气膜冷却叶片上扩散型冷却孔对紊流流场的影响

带有护散型冷却孔的气膜冷却叶版是新开发的结构，用于具有很市初始温度（1700℃）的氢气燃气轮机，名古屋工业大学流体机械实验室在日本首次对该结构的流场进行了研究。用垂直型和X型的热线测量了流场，获得了主流方向平均速度，紊流强度和雷诺剪应力，在沿下游方向和展向方向的平面里分别整理了实验数据，证实了扩散冷却孔对改善燃气轮机膜冷却紊流流场的效果。

Effect of Diffusively Shaped Holes on the Turbulent Flow Field of a Film Cooling Plate

The gas turbine blades with diffusion film cooling holes are newly developed blade structures in the hydrogen combustion gas turbine, which has an extremely high inlet gas temperature (1700°C). The Fluid Machinery Laboratory of Nagoya Institute of Technology conducted firstly a new research on the turbulent flow field over the gas turbine blade with diffusion film cooling holes in Japan. Normal-type and X-type hot wires were applied in the measurement of the flow field. The streamwise mean velocity, the turbulent intensities and the Reynolds shear stress were obtained. The experimental data were processed as spatial distributions in the planes of downstream direction and spanwise respectively. The effect of the diffusion hole on the improvement of the turbulent flow field for the film cooling of gas turbines was demonstrated.