Patent ID: 8127525
Filing Date: 2012-03-06
Classification: F01D,F05D

Abstract:
1. 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 including a stator vane provided on an annular platform of an exhaust casing, this device being for the event of said shaft breaking and comprising: a first braking member, secured to a downstream radial flange of said rim and provided with at least one cutting element comprising teeth extending towards a downstream direction and inclined in a rotating direction of the disk with respect to an axis of rotation of the disk; 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 ring-shaped element extending towards an upstream direction with an upstream radial face perpendicular to the axis of rotation and a downstream face secured to a radial flange part of a radial flange provided on the exhaust casing, the radial flange being disposed radially below the annular platform, wherein the two braking members come into contact with one another through axial displacement of the rotor once the shaft has broken such that the cutting element of the first braking member cuts the ring-shaped element of the second braking member.