采用数值模拟方法，基于建立的等离子体气动激励器模型，探究了横流通道进气条件下等离子体气动激励对气膜冷却特性的影响。结果表明，横流通道进气腔冷却结构气膜孔出口附近存在四支涡结构，起源于孔内边界层流向旋度以及主流与射流剪切作用，涡尺寸、强度和演化过程受横流强度和吹风比的影响较大；施加等离子体激励后，在气膜孔出口附近形成了反肾形涡对，使得气膜对壁面的贴附效果增强，覆盖范围扩大，壁面气膜冷却效果均有所提高，但激励前后对孔流量系数影响不大；吹风比小于1.0时采用低雷诺数横横流通道射流进气腔获得的冷却效率较高，吹风比大于1.0时高雷诺数横横流通道射流进气腔的冷却效率较高。

Using numerical simulation methods, the influence of plasma aerodynamic actuator on the flow characteristics of film cooling under coolant crossflow condition is explored based on the established plasma aerodynamic actuator model. The variation law of film cooling efficiency is obtained. The results show that there are four vortices near the outlet of the film cooling hole, originating from the streamwise vorticity of the boundary layer inside the film cooling hole and the shear effect between the main flow and the jet flow. The size, strength, and evolution process of the vortices are affected by the coolant crossflow channel Reynolds number and blowing ratio. After applying plasma excitation, a new pair of vortices of which the rotating direction is opposite to the counter-rotating vortex pair is formed, the wall attachment of jet is enhanced and spanwise expansion capacity of jet flow is strengthened, thus the film cooling effectiveness is improved. The plasma aerodynamic actuator has little effect on the discharge coefficient. The film cooling effectiveness under coolant crossflow condition is higher with low Reynolds number when the blow ratio is less than 1.0 while the film cooling effectiveness is higher with high Reynolds number when the blow ratio is larger than 1.0.