METHOD AND DEVICE FOR COOLING SHAFT OF AIRCRAFT GAS TURBINE ENGINE Russian patent published in 2018 - IPC F02C7/47 

FIELD: aircraft engineering.

SUBSTANCE: invention relates to aircraft engineering, namely the supply of a coolant to the shaft of an aircraft gas turbine engine, and can be used in transport engineering. Above method for cooling the shaft of an aircraft gas turbine engine with an internal cavity consists in the following: the shaft is cooled by air withdrawn through the central aperture of the compressor fairing from the entrance to the engine and passing through the inner cavity of the shaft to the region of reduced pressure behind the cut of the jet nozzle. Above method for cooling the shaft of an aircraft gas turbine engine with an internal cavity is realized by means of a device, which comprises inlet fairing of compressor 1 with central air intake hole 2 from engine inlet to inner cavity of shaft 5 and conduit 3 with seal 4 for passage of air through the inner cavity of shaft 5 to the region of reduced pressure behind cutoff of jet nozzle 6 at a distance of ~ 0.75-1.5 of the diameter d of pipeline 3 and cooling of shaft 5.

EFFECT: method makes it possible to improve the cooling of the aircraft gas turbine engine shaft with an internal cavity, while ensuring either an increase in the cyclic life of the shaft, or a decrease in its mass, or the possibility of using less heat-resistant (cheaper) material for its production.

2 cl, 1 dwg