The leading edge of a three-dimensional screwy coolant turbine stator was numerically simulated when the injection angles of the row of holes were 30°

60° and 90° respectively

and the lateral direction angles were all 90°.Source point and hole jet methods were adopted separately to study comparatively the aerodynamic performance and cooling characteristics on the leading edge;the mechanism of coolant injection and the influence of different injection angles on the field of cascade flow and cooling characteristics were analyzed.The results show that film holes influence obviously the flow field near the leading edge of about 10% axial chord length range

and the cooling effect covers the entire leaf.The pressure of source point method is very close to non-cooled turbine.With the decrease of cooling air radial injection angle

the surface temperature of real holes model drops by 8% to 16%

but that of source point model by 21% to 23%.The results of source point method can not be taken as a quantitative basis for assessment in engineering.