Patent ID: 11933191
Assignee: SAFRAN AIRCRAFT ENGINES
Field: Engines, pumps, turbines (Mechanical engineering)
Classification: CPC F | IPC F

Claim 19:
20. A coupling for a turbomachine, comprising:
a first disk and a second disk which extends around an axis while being engaged with each other along the axis, each disk including teeth which extend axially to be engaged axially in a respective concavity of the other disk;
a first cylindrical inner face of the first disk being common to the first teeth; and
a second cylindrical inner face of the second disk being common to the second teeth, wherein
the coupling further comprises at least one blocking member which cooperates with blocking means borne by the teeth of the first and the second disks to block axially the first disk with respect to the second disk,
the blocking member includes a cylindrical bottom with a cylindrical outer surface with a ring shaped rib protruding from the cylindrical outer surface and engaging between the first and second retention faces,
the teeth of each disk have a trapezoidal profile oriented axially towards the other disk, and a protuberance which juts out beyond the end of the trapezoidal profile while extending towards the axis, the protuberances forming the blocking means, and
the blocking member is a split ring.