Patent ID: 11873076
Assignee: SAFRAN AIRCRAFT ENGINES
Field: Engines, pumps, turbines (Mechanical engineering)
Classification: CPC B  F  Y | IPC B  F

Claim 0:
1. An assembly comprising a propeller vane and a system for setting the pitch of the vane, for an aircraft turbine engine, the vane having a root extending from an upper end connected to a blade of the vane to a free lower end, the root having a bulged stretch, referred to as “bulb”, the system for setting the pitch of the vane about a pitch axis, wherein it comprises:
a cup which is radially delimited by an annular wall extending around the pitch axis, the cup comprising a lower bottom enclosed by a bottom wall and an upper opening through which the bulb is intended to be inserted axially into the cup;
an annular retention ring extending around the bulb, the retention ring being at least limited in axial displacement towards the opening with respect to the cup, the retention ring having an annular bearing surface face which restricts the passage cross-section of the opening and which is intended to be in axial contact with an upper face of the bulb to block the axial displacement of the root towards the opening;
a lower seat carried by a part separate from the retention ring by means of which the root is axially supported in the cup in the direction of the bottom, the seat and/or the retention ring being mounted movable in axial translation with respect to the cup by means of at least one clamping mechanism in order to allow the axial clamping of the bulb between the seat and the bearing surface face of the retention ring.