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AssigneeSnecma
InventorsJacques Rene Bart, Didier Rene Andre Escure, Claude Marcel Mons, Stephane Rousselin
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The present invention relates to a device for, in a gas turbine engine, braking a turbine comprising a rotor, having at least one disk (63′) with a rim (63′B), driving a shaft and capable of rotating with respect to a stator, this device being for the event of said shaft breaking and comprising a first braking member (110), secured to said rim and provided with at least one cutting element (110A), and a second braking member (120) secured to the stator downstream of the rim (63′B), comprising a ring-shaped element (120A) made of a material that can be cut by the cutting element (110A), the two braking members coming into contact with one another through axial displacement of the rotor once the shaft has broken, the cutting element (110A) of the first braking member (110) cutting the ring-shaped element (120A) of the second braking member (120).
A device for, in a gas turbine engine, braking a turbine comprising a rotor, having at least one disk with a rim, driving a shaft and capable of rotating with respect to a stator, this device being for the event of said shaft breaking and comprising a first braking member, secured to said rim and provided with at least one cutting element, and a second braking member secured to the stator downstream of the rim, comprising a ring-shaped element made of a material that can be cut by the cutting element, the two braking members coming into contact with one another through axial displacement of the rotor once the shaft has broken, the cutting element of the first braking member cutting the ring-shaped element of the second braking member.
A twin spool gas turbine engine with a low-pressure turbine section in which said section is equipped with a braking device as claimed in one of the preceding claims.
Dependencies are inferred from the claim text.