US 11,808,169 B2
Assembly for a turbomachine
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. 17/614,667
Filed by SAFRAN AIRCRAFT ENGINES, Paris (FR)
PCT Filed May 27, 2020, PCT No. PCT/EP2020/064650
§ 371(c)(1), (2) Date Nov. 29, 2021,
PCT Pub. No. WO2020/239808, PCT Pub. Date Dec. 3, 2020.
Claims priority of application No. 1905734 (FR), filed on May 29, 2019.
Prior Publication US 2022/0228494 A1, Jul. 21, 2022
Int. Cl. F01D 5/26 (2006.01); F01D 5/16 (2006.01); F01D 5/22 (2006.01); F04D 29/32 (2006.01); F04D 29/66 (2006.01)
CPC F01D 5/26 (2013.01) [F01D 5/16 (2013.01); F01D 5/225 (2013.01); F04D 29/324 (2013.01); F04D 29/668 (2013.01); F05D 2220/36 (2013.01); F05D 2230/60 (2013.01); F05D 2240/80 (2013.01); F05D 2260/96 (2013.01)] 13 Claims
OG exemplary drawing
 
1. 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 and;
a second rotor movable in rotation relative to the casing around a longitudinal axis; and
a damper configured to dampen 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 on the first rotor, the first part having a first radially inner surface extending all around the longitudinal axis, a first radially outer surface extending all around the first radially inner surface and a first radial thickness being measured perpendicular to the longitudinal axis between the first radially inner surface and the first radially outer surface;
a second part bearing on the second rotor, the second part having a second radially inner surface extending all around the longitudinal axis, a second radially outer surface extending all around the second radially inner surface and a second radial thickness being measured perpendicular to the longitudinal axis between the second radially inner surface and the second radially outer surface; and
a third part connecting the first part to the second part, the third part having a third radially inner surface extending all around the longitudinal axis, a third radially outer surface extending all around the third radially inner surface and a third radial thickness being measured perpendicular to the longitudinal axis between the third radially inner surface and the third radially outer surface, wherein the third radial thickness is greater than at least one of the first radial thickness and the second radial thickness and the third part further comprises a bulge,
wherein the third part has a first bearing 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.