US Patent 10415671 Gearbox comprising an improved reduction gear

A gearbox for an aircraft turbine engine includes a drive shaft, a secondary drive shaft coupled to the drive shaft with a reduction mechanism, and output shafts, each of which is coupled to the drive shaft or to the secondary drive shaft with a set of ring and pinion gears, wherein the reduction mechanism includes an intermediate shaft, a first end coupled to the drive shaft with a first stage of gears and the second end coupled to the secondary drive shaft with a second stage of gears, and wherein the intermediate shaft is rotatably mounted in the gearbox about the main axis thereof which is oriented substantially perpendicular to the main axis of the drive shaft.