METHOD OF COOLING THE ROTOR OF A HIGH PRESSURE TURBINE (HPT) OF GAS TURBINE ENGINE (GTE), HPT ROTOR AND HPT ROTOR BLADE COOLED BY THIS METHOD, KNOT OF THE DEVICE OF TWISTING OF AIR OF HPT ROTOR Russian patent published in 2019 - IPC F01D5/18 

FIELD: turbines or turbomachines.

SUBSTANCE: method of cooling a high-pressure turbine rotor of a gas turbine engine is carried out by the fact that the rotor is cooled by a secondary air flow from the combustion chamber of the engine gas generator, having a temperature lower than the temperature of the primary flow of the working medium from the flame tube of the combustion chamber. Air flow at the inlet of the air cooling circuit of the high-pressure turbine rotor is supplied through the inlet unit of the air cooling circuit of the nozzle assembly combined with the above path into the unit of the air swirler, which includes two cross-oriented annular conical cavities and an air swirler. At the outlet of the second cavity the cooling air gets into the spinning device and through the system of confuser cylinder-cone nozzles, which are deflected towards the engine outlet and towards the rotation of the high-pressure turbine impeller, enters the annular channel formed by adjacent walls of the high-pressure turbine disk and pressure disc. Further, under pressure, air is directed into system of diffuser channels in disc rim, from which air enters channel in blade root, getting into distributing header in cavity of blade. In the header the cooling air is transformed into two flows. Frontal part of flow is directed through radially oriented row of holes in separating wall to channel of cyclone cooling of inlet edge of feather, cooling it from inside, and through another row of holes in blade root back cooling air is removed from cavity and floor cooling is performed outside of blade root back. Rear bulk of the flow from the dispensing collector enters the vortex matrix supplemented with a vortex generator, cooling the back part of the blade body, and through the slot in the outlet edge of the blade, the exhaust air enters the working medium flow of the turbine flow section.

EFFECT: invention is aimed at improving cooling efficiency of high-pressure turbine high-pressure elements, reliability and service life of high-pressure turbine and engine as a whole.

7 cl, 5 dwg