CPC B64C 11/06 (2013.01) [F01D 7/00 (2013.01); F04D 29/323 (2013.01); F04D 29/644 (2013.01); F05D 2260/70 (2013.01)] | 15 Claims |
1. An assembly for an aircraft turbine engine, the assembly comprising:
an un-ducted propeller vane having a root configured to be attached to a hub of the propeller and which is configured to be received in an associated opening of an external casing of the hub, the root having a bulbous-shaped segment;
a system for setting the pitch of the vane about a setting axis, the pitch setting system comprising a cup which is configured to be arranged inside the external casing, which comprises an open flared upper end for the axial insertion of the root into an annular wall of the cup, and in which the root of the vane is axially attached by an immobilization member which is attached to the cup, the cup configured to be pivotally mounted about the setting axis with respect to the hub; and
at least one retention prong extending radially from the wall of the cup into a radial space reserved between the wall of the cup and the root, the at least one retention prong being arranged axially opposite the bulb, the at least one retention prong being capable of retaining the root of the vane inside the cup by contact with the bulb in the event of failure of the immobilization member,
wherein the at least one retention prong can bend to dampen a displacement of the root of the vane axially in the event of failure of the immobilization member.
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