US Patent 12103709 Pre-assembly method for an aircraft turbomachine

A pre-assembly method for an aircraft turbomachine, including preliminarily assembling, outside the turbomachine, the following components with each other: a reduction gear configured to transmit a rotation between at least two rotors of the turbomachine while modifying the speed and torque ratio from one to the other of the at least two rotors, a shaft kinematically coupled to the reduction gear and configured to be kinematically coupled to one of the at least two rotors, a bearing support, and at least one bearing mounted on the bearing support and configured to rotatably support the shaft.