Patent ID: 11891967
Assignee: SAFRAN AIRCRAFT ENGINES
Field: Engines, pumps, turbines (Mechanical engineering)
Classification: CPC F  B  Y | IPC B  F

Claim 0:
1. A turbofan, comprising a fan, a casing positioned downstream of the fan and separating a primary flowpath from a secondary flowpath, a compressor, a combustion chamber and a turbine being arranged in the primary flowpath, the turbofan comprising a differential transmission coupled to the turbine, and a power supply device configured to provide additional power to that provided by the turbine to drive the compressor, wherein the differential transmission comprises a first reduction gear configured to modify the rotation speed transmission ratio between the turbine and the fan and a second reduction gear configured to modify the rotation speed transmission ratio between the turbine and the compressor, the second reduction gear being coupled to an output of the first reduction gear different from an output coupled to fan.