Torque split gearbox for rotary wing aircraft

摘要

A gearbox system for a dual coaxial counter rotating rotor assembly includes an input shaft to input a first torque into the gearbox system and a transfer shaft operably connected to the input shaft to transfer the first torque therethrough. Two gear sets are operably connected to the transfer shaft. Each gear set includes a first output gear to transfer a second torque acting in a first direction to a first rotor of a rotor assembly and a second output gear to transfer the second torque acting in a second direction opposite the first direction to a second rotor of the rotor assembly. The second torque transferred by each gear set of the two gear sets is substantially equal.

主权项

1. A rotary wing aircraft, comprising:
an airframe; a rotor assembly including a first rotor rotatable about a rotor axis in a first direction and a second rotor coaxial with the first rotor and rotatable about the rotor axis in a second direction opposite the first direction; and a drive system including plural engines outputting torque and a gearbox assembly to reduce torque produced from one or more of the engines to a reduced torque and to transfer the reduced torque to the rotor assembly, the gearbox assembly comprising: an input shaft to input the torque into the gearbox assembly; an input bevel shaft operably connected to the input shaft to transfer the torque therethrough; and two gear sets operably connected to the input bevel shaft, each gear set including first and second intermediate shafts, the first intermediate shaft having a first intermediate idler meshed with a transfer gear of the input bevel shaft and a first output pinion to transfer the reduced torque to the first rotor, and the second intermediate shaft having a first intermediate gear meshed with the first intermediate idler and a second output pinion to transfer the reduced torque to the second rotor.