US 11,746,657 B2
Turbomachine rotor
Alexandre Auduberteau, Moissy-Cramayel (FR); Julien Fabrice Girardot, Moissy-Cramayel (FR); and Pierre Chabanne, Moissy-Cramayel (FR)
Assigned to SAFRAN HELICOPTER ENGINES, Bordes (FR)
Appl. No. 17/311,609
Filed by SAFRAN HELICOPTER ENGINES, Bordes (FR)
PCT Filed Dec. 3, 2019, PCT No. PCT/FR2019/000197
§ 371(c)(1), (2) Date Jun. 7, 2021,
PCT Pub. No. WO2020/115373, PCT Pub. Date Jun. 11, 2020.
Claims priority of application No. 1872559 (FR), filed on Dec. 7, 2018.
Prior Publication US 2022/0034228 A1, Feb. 3, 2022
Int. Cl. F01D 5/02 (2006.01); F01D 5/10 (2006.01)
CPC F01D 5/023 (2013.01) [F01D 5/10 (2013.01); F05D 2240/55 (2013.01); F05D 2240/61 (2013.01); F05D 2260/96 (2013.01)] 17 Claims
OG exemplary drawing
 
1. A turbomachine rotor (1), characterised in that it comprises:
a threaded or tapped part (3, 6); and
a damping nut (8) screwed onto the threaded or tapped part (3, 6) so as to allow threads of the nut (8) and of the threaded or tapped part (3, 6) to rub against one another in the event of vibration of the rotor (1), the nut (8) comprising:
a stop (10) capable of bearing axially on a complementary stop (5) of the threaded or tapped part (3) so that friction between the stop (10) and the complementary stop (5) occurs when the threaded part (3) is in rotation, the stop of the nut (8) being formed by a radially extending flange (10), the stop (5) of the threaded part (3) being formed by an end surface (5) or a radial shoulder, the threaded or tapped part (3) comprising an end area comprising external teeth (4).