CPC B64C 11/06 (2013.01) [F01D 5/30 (2013.01); F01D 7/00 (2013.01)] | 14 Claims |
1. A system for controlling pitch of a propeller vane for an aircraft turbine engine, the system comprising:
a cup having an annular wall extending about a pitch setting axis of the vane, the annular wall comprising a lower axial end enclosed by a bottom wall and an upper axial end that is open and configured to allow a root of the vane configured to be mounted inside the cup, the bottom wall being configured to cooperate in a form-fitting manner with a free end of the root so that the cup is secured in rotation to the root about the pitch setting axis; and
an immobilization ring extending about the pitch setting axis and configured to be mounted about the root, the immobilization ring being configured to be mounted within the cup and to cooperate with the root and the annular wall of the cup, respectively, to ensure axial retention of the root within the cup,
wherein the immobilization ring is a double dog clutch ring which comprises first and second annular rows of external dog teeth, the first annular row of external dog teeth being configured to cooperate by dog clutch with complementary first internal dog teeth of the annular wall of the cup and by an axial support with the complementary first internal dog teeth to ensure axial retention of the root in the cup, and the second annular row of external dog teeth being configured to cooperate by dog clutch with complementary second internal dog teeth of the annular wall of the cup and being spaced from the complementary second internal dog teeth by an axial clearance to ensure a safety in the event of failure of the first annular row of external dog teeth.
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