CPC F01D 5/10 (2013.01) [F01D 5/30 (2013.01); F05D 2220/323 (2013.01); F05D 2240/24 (2013.01); F05D 2260/96 (2013.01)] | 20 Claims |
13. A compressor rotor for aircraft turbomachine extending longitudinally along an axis X, said rotor comprising a damping device and a rotor disc extending transversally relative to the axis X and having a plurality of blades and a plurality of housings formed on an outer periphery of the rotor disc, each of said plurality of blades extending radially with respect to the axis X and comprising a mounting root mounted to one of said housings, a platform, and a radially exterior air deflector vane, wherein the damping device comprises:
a support ring extending transversally relative the axis X and positioned on an outer periphery of the rotor disc; and
a plurality of damping members attached to and extending upstream of the support ring, each of the plurality of damping members positioned under at least one platform of a blade to exert a radial force to dampen the radial displacement of said blade when the turbomachine is in operation.
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