Using infrared thermal imaging technology, the film cooling performance of turbine guide vanes with leading edge counterinclined structure in a cascade wind tunnel was tested. There were 5 rows of compound angle film holes arranging on the leading edge of the vane to form a counterinclined structure,which was characterized that both the radial angles of upper and lower film apertures in the blade height direction were inclined to the middle section. The suction side and the pressure side were arranged with 5 rows and 16 rows of circular holes respectively.The Reynolds numbers of tested cascade inlets were 1.2×105, 2.4×105 and 3.6×105, the blowing ratios were 1.0, 1.5 and 2.0. The experimental results show that the cold air flowing from leading edge counterinclined structure gathers on the middle section of the suction surface and the pressure surface, resulting in an enhanced air film covering effect in the middle section area. When the blowing ratio is 1.0, the heat transfer coefficient at the middle section of the leading edge and the pressure surface is low. 〖JP2〗With the increase of blowing ratio, the heat transfer at the middle section is enhanced,the high heat exchange area of〖JP〗 pressure surface and suction surface becomes longer along the flow direction. When the Reynolds number is 1.2×105, the air film covering on the pressure surface is divergent; when the Reynolds numbers are 2.4×105 and 3.6×105, the air film coverage width of the pressure surface narrows first and then widens along the flow direction.