US 11,808,170 B2
Turbomachine assembly having a damper
Philippe Gérard Edmond Joly, Moissy-Cramayel (FR); Romain Nicolas Lagarde, Moissy-Cramayel (FR); Jean-Marc Claude Perrollaz, Moissy-Cramayel (FR); Laurent Jablonski, Moissy-Cramayel (FR); François Jean Comin, Moissy-Cramayel (FR); Edouard Antoine Dominique Marie De Jaeghere, Moissy-Cramayel (FR); and Charles Jean-Pierre Douguet, Moissy-Cramayel (FR)
Assigned to SAFRAN AIRCRAFT ENGINES, Paris (FR)
Appl. No. 17/614,812
Filed by SAFRAN AIRCRAFT ENGINES, Paris (FR)
PCT Filed May 27, 2020, PCT No. PCT/EP2020/064646
§ 371(c)(1), (2) Date Nov. 29, 2021,
PCT Pub. No. WO2020/239804, PCT Pub. Date Dec. 3, 2020.
Claims priority of application No. 1905745 (FR), filed on May 29, 2019.
Prior Publication US 2022/0228495 A1, Jul. 21, 2022
Int. Cl. F01D 5/26 (2006.01); F01D 5/10 (2006.01); F04D 29/66 (2006.01)
CPC F01D 5/26 (2013.01) [F01D 5/10 (2013.01); F04D 29/668 (2013.01); F05D 2220/36 (2013.01); F05D 2230/60 (2013.01); F05D 2240/30 (2013.01); F05D 2250/71 (2013.01); F05D 2260/96 (2013.01)] 18 Claims
OG exemplary drawing
 
18. A turbomachine assembly comprising:
a casing;
a first rotor comprising a disk and a plurality of blades, the first rotor being movable in rotation relative to the casing;
a second rotor movable in rotation relative to the casing around a longitudinal axis;
a damper configured to damp a movement of the first rotor relative to the second rotor in a plane orthogonal to the longitudinal axis, the movement being caused by a flapping of at least one of the plurality of blades relative to the disk, the damper comprising:
a first part bearing against the first rotor and being configured to apply a first centrifugal force on the first rotor;
a second part bearing against the second rotor and being configured to apply a second centrifugal force on the second rotor; and
a linking part connecting the first part to the second part, the linking part being thinned relative to the first part and the second part; and
a flyweight fixedly mounted on the damper;
wherein:
the first part has a first surface arranged to apply a first force on the second rotor, the first force having a first longitudinal component in a first direction parallel to the longitudinal axis, and a first radial component in a second direction orthogonal to the longitudinal axis, the first longitudinal component being greater than the first radial component;
the second part has a second surface arranged to apply a second force on the second rotor, the second force having a second longitudinal component in the first direction and a second radial component in the second direction, the second radial component being greater than the second longitudinal component.