The invention discloses a novel cooling hole capable of improving the
cooling efficiency of an air film of a
turbine engine. The novel cooling hole structurally comprises conical holes and a rectangular
transverse groove. The rectangular
transverse groove is formed in the conical holes along the direction perpendicular to the flowing direction of
cold air. An included angle between the axis of each hole and a plane ranges from 10 degrees to 40 degrees, the conical holes are machined on the basis of cylindrical holes, an orifice of each conical hole is a conical opening with an opening angle which ranges from 10 degrees to 20 degrees, and the depth of the
transverse groove ranges from 0.5D to 1.0D. Compared with conventional cylindrical air film hole structures, the novel cooling hole has the advantages that the exit sectional area is increased by the conical
nozzle holes, so that the main flow penetrating ability of
jet flow is reduced, reverse vortex pairs around the
nozzle holes can be effectively suppressed, and accordingly the
cooling efficiency can be improved; vertical fixed walls of the transverse groove at the lower edges of the conical holes can stop cooling air flow from flowing, so that parts of the cooling air flow flow to two sides of the novel cooling hole, and the novel cooling hole is favorable for transversely diffusing the cooling air flow; the
cooling efficiency of the novel cooling hole can be improved by about 300% as compared with the traditional cylindrical air film hole under the condition of a certain blowing ratio.