The adiabatic film effectiveness η of the counter-inclined film-holes fed by varying intal coolant intake on the turbine vane leading edge model was experimentally investigated.A semi-cylinder model was adopted to model the vane leading edge which was arranged with two-row holes,which located at ±15° on both sides.The four Leading edge model with the combinations of hole-shape (simple holes and laid-back holes) and intake structure (plenum and impingement) were tested under four blowing ratios M of 0.5,1.0,1.5,and 2.0.The η contours were obtained by the transient measurement technique based on double thermochromic liquid-crystals.The results present that the η is sensitive to the M for the four studied leading edge cases.The addition of impingement enhances the η for the two studied holes.The film jets make the coolant-flow closed to the target surface,resulting in higher η under lower M.The core with higher η appears in the downstream area of hole-exit.The η enhancement can be provided to almost the identical level by adding the impingement-holes and improving the hole-exit shaping in most areas.With increasing M,the jets with stronger exit normal momentum penetrate into the main-flow.The impingement addition may be a more effective program to upgrade the η relatively to the exit shaping under larger M.Besides,the laid-back holes with impingement case produce the highest film cooling performance among the four cases,providing great potential in the leading edge especially under larger M.