FIELD: mechanical engineering; gas-turbine engines. SUBSTANCE: proposed cooling device of gas-turbine engine profile part has wall with front edge area provided with curved outer surface whose center of curvature is arranged inside profile part of blade. Several channels for cooling air made in wall in front edge area form a system of channels. Each channel has straight cylindrical calibrated section with hole and diffuser zone forming outlet hole at intersection with curved surface of wall. Diffuser zone is made in form of part of cone. Axis of cone coincides mainly with axis of channel and is located on part of wall arranged below along cooling air flow at outlet hole of channel. EFFECT: increased efficiency of cooling. 6 cl, 8 dwg
