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.
TORQUE SPLIT GEARBOX FOR ROTARY WING AIRCRAFT
02.06.2016
Patent
Elektronische Ressource
Englisch
PROPELLER GEARBOX OIL COOLER FOR A ROTARY WING AIRCRAFT
Europäisches Patentamt | 2018
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