FIELD: mechanical engineering; gas turbines.
SUBSTANCE: proposed cooling system contains great number of blades forming great number of nozzles of gas turbine. Each blade has concave and opposite convex surfaces which are united to form outer shape of blade. Blade is provided with great number of cooling holes in communication with cooling liquid medium inside said blade and opening through concave surface of blade. Each cooling hole has inlet section inside blade and outlet section opening through concave surface. Cross section of cooling hole changes in radial direction. Height of inlet section along mainly radial direction of blade is less than height of outlet section, thanks to which thickness of wall between cooling hole and concave surface in area of outlet section decreases.
EFFECT: possibility of exclusion of undesirable temperature gradients inside blade and reduction of thickness of material near cooling holes of trailing edge.
3 cl, 4 dwg
