FIELD: aircraft industry.
SUBSTANCE: unit of gas-turbine engine of flying vehicle contains high-pressure stage including high-pressure turbine with possibility of transmission of drive force connected with high-pressure compressor by high pressure shaft and rotating around engine centerline, low-pressure turbine with flow path of low-pressure turbine and arranged after high-pressure stage. Low-pressure turbine has turbine with low-pressure inner and outer shafts rotating in opposite directions including rotors of turbines rotating in opposite directions, respectively, with inner and outer low-pressure shafts which are, at least partially, arranged for rotation coaxially with high-pressure stage and in radial direction inside relative to stage. Rotor of turbine with low-pressure inner shaft includes first blade rims of low-pressure turbine connected to transmit drive force with blade rim of first fan by means in low-pressure shaft. Rotor of turbine with low-pressure shaft includes second blade rims of low-pressure turbine connected for transmission of drive force with blade rim of second fan by outer low-pressure shaft. At least one row of low-pressure turnable blades is arranged across flow path of low-pressure turbine between adjacent pair of one of first blade rims of low-pressure turbine with inner shaft and one of second blade rims of low-pressure turbine with outer shaft.
EFFECT: improved efficiency of fan in operation.
10 cl, 10 dwg
