TURBINE OF DOUBLE-ROTOR GAS TURBINE ENGINE Russian patent published in 2014 - IPC F02C7/06 F02C7/28 F01D25/16 F01D25/18 

FIELD: engines and pumps.

SUBSTANCE: turbine of a double-rotor gas turbine engine comprises an external body, an air header, a pre-oil and an oil cavities, rotors of high and low pressures, channels of oil supply into roller bearings, oil seals, a wheelspace labyrinth seal, feed nozzles. In accordance with the stated proposal the turbine is equipped with a support circular shell with a radial collar, a circular nut with a radial collar on its side surface, a support bushing and a radial-end oil seal. The support bushing is installed on the shaft of the high pressure rotor and is fixed by a circular nut. The support circular shell is made as a whole with the shaft of the low pressure rotor and is installed to form an upper oil bath. The radial-end oil seal is made in the form of two step-bearings with graphite sealing rings and a spacer bushing with a fixing spring arranged between them. Oil seals between the pre-oil and oil cavities are made in the form of bracelet graphite seals. In the support circular shell and in the step-bearing adjacent to the end of the shaft of the low pressure rotor there are holes communicated with each other. The circular nut is installed to form a middle oil bath. Feed nozzles are placed opposite to the middle oil bath.

EFFECT: reduced oil heating in an oil cavity, reduced non-return oil flow, increased environmental compatibility of an engine and reduction of its visibility.

3 dwg