US 11,808,212 B2
Drive shaft comprising a fusible section and method for protecting such a drive shaft against an overtorque
Arnaud Nicolas Negri, Moissy-Cramayel (FR); Julien Fabien Patrick Becoulet, Moissy-Cramayel (FR); Michel Gilbert Roland Brault, Moissy-Cramayel (FR); and Romain Guillaume Cuvillier, Moissy-Cramayel (FR)
Assigned to SAFRAN AIRCRAFT ENGINES, Paris (FR)
Appl. No. 17/431,896
Filed by SAFRAN AIRCRAFT ENGINES, Paris (FR)
PCT Filed Feb. 19, 2020, PCT No. PCT/FR2020/050309
§ 371(c)(1), (2) Date Aug. 18, 2021,
PCT Pub. No. WO2020/169927, PCT Pub. Date Aug. 27, 2020.
Claims priority of application No. 1901776 (FR), filed on Feb. 21, 2019.
Prior Publication US 2022/0145805 A1, May 12, 2022
Int. Cl. F02C 7/36 (2006.01); F16C 3/02 (2006.01); F16D 9/08 (2006.01)
CPC F02C 7/36 (2013.01) [F16C 3/023 (2013.01); F16D 9/08 (2013.01); F05D 2240/60 (2013.01); F16C 2326/43 (2013.01)] 14 Claims
OG exemplary drawing
 
1. A drive shaft of an aircraft turbomachine, comprising:
a first portion extending longitudinally along an axis and having a first diameter,
a second portion extending longitudinally along said axis and having a second diameter, and
connecting means connecting said first and second portions and being configured to transmit a torque from said second portion to said first portion, said connecting means comprise at least one bellows comprising:
a first section extending longitudinally along said axis and having a diameter greater than said first and second diameters, and
second sections extending radially to said axis and flanking said first section,
wherein said first section comprises at least one fusible section comprising at least one through orifice and being configured to break when the value of a torque applied to said first portion exceeds a predetermined threshold value.