Patent ID: 7363757

Claim:
A turbine engine with a semi-fixed turbine for aircraft, configured to drive a receiver in order to preserve a roughly constant rotation speed, the turbine engine, comprising: an LP compressor; an HP compressor; a combustion annulus; an HP turbine; and an LP turbine which, via a gear system, is configured to drive the receiver and the LP compressor, wherein the gear system has a torque control system configured to maintain a constant ratio between a driver torque of the receiver transmitted by the gear system and a driver torque of the LP compressor transmitted by the gear system and the torque control system is further configured to decrease a rotation speed of the LP compressor while maintaining a rotation speed of the receiver roughly constant, wherein the gear system has an inlet integral with an LP turbine shaft as well as first and second outlets, the first outlet being integral with an LP compressor shaft and the second outlet being integral with a receiver shaft, and wherein the torque control system has a satellite carrier connected to the entrance of the gear system and with a multiplicity of satellite pinions engaging with a planetary pinion linked to the first outlet of the gear system and with a crown gear connected to the second outlet of the gear system.