Patent ID: 8814502
Filing Date: 2014-08-26
Classification: F02C,F05D

Abstract:
1. A mechanical drive system of an aircraft gas turbine engine comprising: a tower shaft disposed at a non-zero angle with respect to and operatively connected to a main shaft of the engine and first and second bevel gears mounted on the tower shaft, the tower shaft rotating together with said first and second bevel gears at a first rotational speed; an accessory drive gearbox including first and second shafts having respective rotational axes, the rotational axes of the first and second shafts in combination with a rotational axis of the tower shaft defining a common plane, a third bevel gear mounted on the first shaft and meshing with the first bevel gear on the tower shaft, and a fourth bevel gear mounted on the second shaft and meshing with the second bevel gear on the tower shaft, the first shaft rotating at a second rotational speed and the second shaft rotating at a third rotational speed, wherein the second rotational speed is lower than the first rotational speed and wherein the third rotational speed is equal to or higher than the first rotational speed.