RADIAL SECOND MOTION FAN GAS-TURBINE ENGINE CONSTRUCTION Russian patent published in 2017 - IPC F02K3/02 

FIELD: engines and pumps.

SUBSTANCE: engine comprises a compressor unit, a combustion chamber that is in fluid communication with a compressor unit, a turbine unit that is in fluid communication with a combustion chamber, a fan and a velocity variations system that is operated by a fan drive turbine for fan axis rotation. The turbine unit comprises a fan drive turbine and a second turbine. The fan drive turbine comprises a plenty of turbine stages. The fan comprises a plenty of blades that are about an axis rotated. The ratio of fan blades quantity to a number of fan drive turbine stages is from 2.5 to 8.5. The fan drive turbine comprises the first backside rotor that is attached to the first shaft, and the second turbine comprises the second backside rotor that is attached to the second shaft. In front of the first junction between the first backside rotor and the first shaft in the axial direction there is the first bearing unit, and after the second junction between the second backside rotor and the second shaft in the axial direction there is the second bearing unit.

EFFECT: gas-turbine engine operating properties amplification and productivity improvement.

20 cl, 12 dwg, 1 tbl