COOLED HIGH PRESSURE TURBINE VANE Russian patent published in 2022 - IPC F01D5/18 

FIELD: aircraft engine building.

SUBSTANCE: invention relates to the field of aircraft engine building, and in particular to designs of cooled nozzle blades. A cooled nozzle blade of a high-pressure turbine, containing an upper and lower shelves, between which there is a hollow airfoil, made in one piece with the upper and lower shelves, and the airfoil has an internal radial partition, made in one piece with the airfoil, separating the hollow airfoil front and rear internal cavities relative to the forced air flow, wherein the rear inner cavity of the airfoil is equipped with a deflector, the front inner cavity of the airfoil contains perforated holes, in contrast to the known, the front inner cavity of the airfoil contains additional radial partitions made in one piece with the airfoil, arranged in such a way that they form a cavity for cooling the leading edge of the airfoil, a cooling cavity along the back of the airfoil and a cooling cavity along the trough of the airfoil, at the same time, the cooling cavity of the leading edge of the airfoil is made with the possibility of overlapping with the help of a plate, the cooling cavities along the back and along the trough are made with the possibility of overlapping with the help of an overlap element, the element of overlapping of the cooling cavities along the back and along the trough is made in the form of an elongated flange in the upper part of the deflector installed in the rear inner cavity of the airfoil, and connected by a permanent connection with the upper part of the blade airfoil, and at the same time, the cooling cavity of the leading edge of the blade airfoil is made with the possibility of overlapping by means of a plate in the lower part, the element of overlapping of the cooling cavities along the back and along the trough is made in the form of a plate in the lower part of the blade installed in the rear inner cavity of the airfoil by means of a permanent connection with the lower part of the blade airfoil, and at the same time, the cooling cavity of the leading edge of the blade airfoil is made with the possibility of overlapping by means of a plate in the upper part of the airfoil.

EFFECT: invention provides an increase in the stability of the thermal state, the hydraulic characteristics of the nozzle apparatus and the cooling efficiency of the blade airfoil, due to the efficient distribution of cooling air.

3 cl, 6 dwg