AIRCRAFT TURBINE ENGINE INCORPORATING CONTRA-ROTATING CONTROLLED-TORQUE-DIVISION LOW-PRESSURE TURBINES AND AUXILIARY COMPRESSOR ARRANGED BEHIND ROTATING FANS Russian patent published in 2008 - IPC F02K3/72 

FIELD: engines and pumps, transportation.

SUBSTANCE: aircraft turbine assembly incorporates a high-pressure stage comprising a high-pressure turbine coupled, via a high-pressure shaft, with a high-pressure compressor, a low-pressure turbine and a unit-directional rotation auxiliary compressor. The said low-pressure turbine incorporates the turbines with contra-rotating low-pressure inner and outer shafts arranged so as to run, at least, coaxial with the aforesaid high-pressure stage and radially inside it. The low-pressure inner shaft turbine is coupled, via the low-pressure inner shaft, with the front fan blade rim to transmit the driving force. The low-pressure outer shaft turbine is coupled, via the low-pressure outer shaft, with the rear fan blade rim to transmit the driving force. The auxiliary compressor incorporates, at least, one first rotating blade rim coupled with the low-pressure outer shaft to transmit the driving force and arranged axially behind and downstream of the rear fan blade rim. At least, one rim of the low-pressure turbine controlled guide blades is arranged crosswise the low-pressure turbine flow passage between the low-pressure inner and outer shafts turbines.

EFFECT: higher fan efficiency.

13 cl, 8 dwg