US 11,808,165 B2
Aircraft turbomachine rotor comprising a damping device
Nicolas Gérard Bénito Cornec, Moissy-Cramayel (FR)
Assigned to SAFRAN AIRCRAFT ENGINES, Paris (FR)
Appl. No. 17/436,349
Filed by SAFRAN AIRCRAFT ENGINES, Paris (FR)
PCT Filed Mar. 4, 2020, PCT No. PCT/EP2020/055599
§ 371(c)(1), (2) Date Sep. 3, 2021,
PCT Pub. No. WO2020/178300, PCT Pub. Date Sep. 10, 2020.
Claims priority of application No. 1902260 (FR), filed on Mar. 6, 2019.
Prior Publication US 2022/0162946 A1, May 26, 2022
Int. Cl. F01D 5/10 (2006.01); F01D 5/30 (2006.01)
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
OG exemplary drawing
 
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.