METHOD FOR COOLING HIGH-PRESSURE TURBINE NOZZLE ASSEMBLY (TNA) OF GAS TURBINE ENGINE (GTE) AND NOZZLE DEVICE OF GTE TNA (EMBODIMENTS)

摘要

FIELD: machine building.;SUBSTANCE: method of cooling high-pressure turbine nozzle assembly is performed by cooling the most heat-stressed elements in blades and flanges of nozzle unit nozzle blocks by two air flows - secondary air flow of combustion chamber and air from air-to-air heat exchanger. Flanges of the blocks extending into the flow part of the nozzle apparatus are washed with floor jets of cooling air of the combustion chamber, which comes from the large and small air intake rings. In the block large shelf the cooling air is supplied through the nozzle device outer ring. One part of the air flow penetrates through groups of screen holes into the sub-screen cavity and cools the bottom of the large shelf. Other part of the air flow from the above-screen cavity of the flange enters the front cavity of the blade, fills the volume of the diagonally truncated deflector, and exits the deflector, cools the input edge of the airfoil, which is equipped with seven rows of holes, which are inclined to the flow of the working medium. Deflector diagonally divides the front cavity diagonally with the back for back cooling of walls of the diagonal parts of the cavity. Excess heat is removed from the front part of the back and the trough of the blade body by counter-flowing the first air flow into the front cavity coming through the slit-hole in the small flange. In the front cavity the back and trough of the blade body are provided with two and four rows of holes. Flow of cooling air from the air-air heat exchanger enters the back cavity of the vane via the outer ring of the nozzle device to form a branched air path. Rear cavity of blade is equipped with deflector provided with perforated holes to vortex matrix and intended for cooling with smaller part of flow of rear part of blade and with larger part of flow of cooling of high pressure turbine rotor.;EFFECT: invention is aimed at improving cooling efficiency of high-pressure turbine nozzle assembly cooling elements.;9 cl, 5 dwg