高压涡轮动叶吸力面气膜冷却特性研究

Film Cooling Characteristics of the Suction Surface of a High Pressure Turbine Rotor Blade

为了研究某航空发动机高压涡轮动叶吸力面的气膜冷却特性,通过数值模拟的方法,采用SST k-ω湍流模型,分析了高压涡轮动叶在静止和旋转条件下,吸力面气膜冷却效率的影响规律。结果表明:在静止条件下,相同主流湍流度时吹风比对吸力面气膜冷却效率影响显著,冷却效率随着吹风比的增大而减小;在小吹风比下,气膜冷却效率随着主流湍流度的增大而减小;在大吹风比下,气膜冷却效率随着主流湍流度的增大而增大。在相同湍流度和转速下,随着吹风比的增大,气膜向高半径偏转程度减小;在相同湍流度和吹风比下,随着转速的增大,气膜沿流向上的气膜覆盖面积减弱。优化结构的扇形气膜孔对叶片吸力面具有更好的冷却效果。

In order to study the film cooling characteristics of an aero-engine high pressure turbine rotor blade suction surface,with the SST k-ωturbulence model the numerical simulation was used to analyze the influence of film cooling efficiency on the suction surface of a high pressure turbine rotor blade under static and rotating conditions.The results show that:under the static condition,the blowing ratio has a significant effect on the film cooling efficiency of the suction surface with the same mainstream turbulence,and the cooling efficiency decreases with the increase of the blowing ratio;at a low blowing ratio,the film cooling efficiency decreases with the increase of the mainstream turbulence;at a high blowing ratio,the film cooling efficiency increases with the increment of the mainstream turbulence.At the same turbulence intensity and rotation speed,the deflection degree of film to high radius decreases with the increment of blowing ratio;at the same turbulence intensity and blowing ratio,the film coverage along the flow direction decreases with the increase of rotation speed.The fan-shaped air film holes with optimized structure have a better cooling effect on the suction surface of the blade.