CPC B64C 11/06 (2013.01) [F04D 29/323 (2013.01)] | 12 Claims |
1. A system for controlling a pitch setting of a propeller vane for an aircraft turbine engine, the system comprising:
a vane including a blade connected to a root;
a cup including an annular wall extending around a pitch axis of the vane, the annular wall having a lower axial end closed by a bottom wall, and an upper axial end which is open and configured to allow mounting of the root of the vane inside the cup, the bottom wall including a recess having a non-circular cross-section and configured to receive a free end of a complementary shape of the root so that the cup is secured in rotation to the root about the pitch axis;
an immobilization ring extending around the pitch axis and mounted around the root, the immobilization ring being mounted within the cup and cooperating respectively with the root and the annular wall of the cup to ensure the axial retention of the root in the cup; and
at least one safety element configured to ensure retention of the root from the cup, the at least one safety element having a generally elongated shape and extending transversely to the pitch axis, the at least one safety element passing through aligned orifices in the bottom wall of the cup as well as an orifice in the free end of the root.
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