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 |
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.
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