FIELD: engines and pumps.
SUBSTANCE: two-rotor gas-turbine engine contains low and high pressure rotors installed with a possibility of rotation in a fixed case. The low pressure rotor contains a compressor and a turbine connected with the low pressure shaft supported by the forward support bearing, and also by the first back and additional back support bearings. The first back support bearing and the additional back support bearing are supported by an exhaust case of the fixed case. The high pressure rotor is installed on forward and back support bearings of the high pressure rotor. The back support bearing of the high pressure rotor is the intershaft support bearing containing the inner race rigidly fixed to the high pressure turbine rotor, and the outer race, rigidly fixed to the low pressure shaft.
EFFECT: invention allows to decrease radial gaps on the ends of rotor blades under the load resulted from aircraft manoeuvring.
7 cl, 5 dwg
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