US 2026/0309048 A1Published application

System for locking a plug in a component of an aircraft turbine engine, preferably a turbine engine shaft

AssigneeSafran Aircraft Engines

InventorsThomas Jérôme George DUNOYER DE SEGONZAC, Thierry FACHAT, Patrick Jean Laurent SULTANA, Fabrice Marcel Noël GARIN

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Abstract

A system for locking a plug on an component of an aircraft turbine engine, including a locking ring equipped with a projecting element, which, in a ring-locking position, is intended to be inserted into a first recess of the component, the first recess opening axially, the plug including a retaining finger intended to be inserted into a second recess of the component, the second recess adopting the form of a second notch circumferentially opening into the first recess. In addition, in the ring-locking position, the projecting element is intended to circumferentially cover, at least partially, the second recess housing the retaining finger of the plug.

Claims10

Dependent claims

A system for locking a plug in a component of an aircraft turbine engine of axis, the component extending circumferentially about the axis,

wherein the system comprises a locking ring equipped with a projecting element, which, in a locking position of the locking ring, is intended to be inserted into a first recess of the turbine engine component, the first recess opening axially, the plug including a retaining finger intended to be inserted into a second recess of the component, the second recess adopting the form of a second notch opening circumferentially in the first recess,
and wherein the locking position of the locking ring in the turbine engine component, the projecting element of the locking ring is intended to circumferentially cover, at least partially, the second recess housing the retaining finger of the plug.

Dependencies are inferred from the claim text.