METHOD FOR COOLING OF NOZZLE ASSEMBLY OF A LOW-PRESSURE TURBINE (LPT) OF A GAS TURBINE ENGINE AND A LPT NOZZLE ASSEMBLY WHICH IS COOLED BY THIS METHOD, A METHOD FOR COOLING A BLADE OF LPT NOZZLE ASSEMBLY AND A NOZZLE ASSEMBLY BLADE, COOLED BY THIS METHOD Russian patent published in 2019 - IPC F01D5/18 

FIELD: aviation.

SUBSTANCE: group of inventions relates to the field of aircraft engine building. LPT nozzle assembly includes nozzle ring formed of nozzle clusters assembled by at least three nozzle blades made as a whole with small and large ones. Nozzle clusters are mounted between outer and inner power rings connected by hollow power pins passed through extreme blades. Transit tube is passed through the middle blade of each cluster. Nozzle blade is equipped with deflector arranged in front part of cavity. Walls of blade are equipped with finning inside forming blade air-cooling tract – system of horseshoe-shaped radiation-convector ribs prolonged into head part of back and trough, and a system of elongated ribs oriented along the flow, on which walls of the deflector are freely supported with provision of the required tract channel height. In the deflector walls over the blade height there is at least one row of front and two ordered systems of side outlet holes in the walls of the deflector. In the method of cooling the nozzle assembly, cooling air is fed from the AATE into the inlet manifold formed by the hollow body of the outer ring NA. From inlet manifold at least half of air flow through transit tubes enters intermediate header of transit path of air cooling of LPT and TPE rotor. Not less than one third of air flow through outlet holes is passed for cooling of large flange and blades of nozzle cluster. Cooling air flow enters the deflector. Through the front holes air enters the head row of channels near the inlet edge of the blade with separation of the tract air cooling path into two inner channels between the deflector and the blade walls. Cooling flow is flowing along inner channels with cooler air along the makeup feedthrough through outlet holes in the deflector sidewalls. Then air is successively supplied to vortex matrix and vortex generator through which air heated by heat removal is directed to total flow of working medium in flow part of LPT.

EFFECT: increased efficiency of cooling of blades of nozzle assemblies, clusters and rotor of LPT.

7 cl, 6 dwg