US 12,103,709 B2
Pre-assembly method for an aircraft turbomachine
Adrien Louis Simon, Moissy-Cramayel (FR); Guillaume Julien Beck, Moissy-Cramayel (FR); Yohan Douy, Moissy-Cramayel (FR); Jordane Emile André Peltier, Moissy-Cramayel (FR); and Jérémy David Seban, Moissy-Cramayel (FR)
Assigned to SAFRAN TRANSMISSION SYSTEMS, Colombes (FR)
Filed by SAFRAN TRANSMISSION SYSTEMS, Colombes (FR)
Filed on May 3, 2023, as Appl. No. 18/311,414.
Claims priority of application No. 22 04242 (FR), filed on May 4, 2022.
Prior Publication US 2023/0356858 A1, Nov. 9, 2023
Int. Cl. B64F 5/10 (2017.01); F02C 7/36 (2006.01); F16H 1/28 (2006.01)
CPC B64F 5/10 (2017.01) [F02C 7/36 (2013.01); F16H 1/28 (2013.01)] 16 Claims
OG exemplary drawing
 
1. A pre-assembly method for an aircraft turbomachine, comprising 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 aircraft turbomachine while modifying a speed and torque ratio from one to another one of said at least two rotors, the reduction gear comprising a stator member,
a shaft kinematically coupled to the reduction gear and configured to be kinematically coupled to one of said at least two rotors,
a bearing support provided with a flange located radially outside the bearing support, the flange being configured to receive fixing elements for dismountably connecting to a casing of the turbomachine,
at least one bearing mounted on the bearing support and configured to rotatably support the shaft, and
an attachment element extending from the stator member to the bearing support so as to fix the stator member to the bearing support, wherein the attachment element extends from one side of the reduction gear to another side of the reduction gear.