Patent ID: 11970983
Assignee: SAFRAN AIRCRAFT ENGINES
Field: Engines, pumps, turbines (Mechanical engineering)
Classification: CPC F | IPC F

Claim 0:
1. An arrangement for an aircraft turbine engine comprising:
a shaft rotating about an axis of rotation:
a following member centered on the axis of rotation and rotatably coupled to the shaft by a splined connection comprising first splines integral with the following member, and second splines integral with the rotating shaft and co-operating with said first splines:
on either side of the splined connection, respectively an upstream connection for radially centering the following member relative to the shaft, and a downstream connection for radially centering the following member relative to the shaft, the upstream and downstream radial centering connections being axially sliding;
a device for spraying a lubricant into a lubricant collection cavity;
a lubricant intake passage made through the rotating shaft or the following member, the lubricant intake passage opening into said lubricant collection cavity, and opening into a spline lubrication cavity delimited in part by the upstream and downstream radial centering connections; and
a lubricant discharge passage made through the rotating shaft or the following member, the lubricant discharge passage opening into said spline lubrication cavity, and opening externally to the arrangement, wherein:
the upstream radial centering connection is made by a first upstream centering portion provided on the following member, and a second upstream centering portion provided on the shaft and cooperating with the first upstream centering portion so as to define an upstream radial clearance within the upstream radial centering connection,
the downstream radial centering connection is formed by a first downstream centering portion provided on the following member, and a second downstream centering portion provided on the shaft and cooperating with the first downstream centering portion so as to define a downstream radial clearance within the downstream radial centering connection, and
each of the upstream and downstream radial clearances is strictly less than radial clearances at an end of each of the first and second splines.