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The present invention relates to a blade retention apparatus for a bladed rotor in a turbine section of a gas turbine engine which comprises a rivet grip which has serration at one end and an upset head at the other end, and a sleeve made of a soft metal which is compressed to the serration actually

The present invention relates to a blade retention apparatus for a bladed rotor in a turbine section of a gas turbine engine which comprises a rivet grip which has serration at one end and an upset head at the other end, and a sleeve made of a soft metal which is compressed to the serration actually against the surfaces of the disk and the blade. The retention apparatus of the present invention provides a reliable attachment and only requires a simple hand-held pneumatic riveting tool to install.

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[ We claim:] [1.] In a bladed rotor for a gas turbine comprising a rotor having an axis of rotation, the rotor including a disc having an annular rim with a plurality of spaced-apart slots extending in the direction of the axis of rotation and blades mounted to the rotor with each blade comprising a

[ We claim:] [1.] In a bladed rotor for a gas turbine comprising a rotor having an axis of rotation, the rotor including a disc having an annular rim with a plurality of spaced-apart slots extending in the direction of the axis of rotation and blades mounted to the rotor with each blade comprising an air foil, a blade platform, and a root inserted in a respective slot, the bladed rotor further comprising a blade retention apparatus extending in interference between the root of the blade and the rim at the slot of the rotor, the disc being provided with countersunk cavities associated with each slot, the blade retention apparatus comprising:a metal shank which has circumferential serrations at one end and an upset head at the other end; anda metal retainer of ductile metal compressed onto the serrations axially within a respective countersunk cavity of the disc and the blade. [8.] A method for retaining a blade in a bladed rotor for a gas turbine comprising a rotor having an axis of rotation, the rotor including a disc having an annular rim with a plurality of spaced-apart slots extending in the direction of the axis of rotation, each blade comprising an air foil, a blade platform, and a root to be inserted in a respective slot in the disc, the disc including countersunk cavities associated with the slots, the method comprising the steps of:(a) inserting the root of the blade in the respective slot of the disc;(b) inserting a metal shank which has serrations at one end and an upset head at the other end in interference between the root of the blade and the slot of the rotor;(c) inserting a metal retainer in the form of a sleeve made of ductile metal onto the serrations of the end of the metal shank; and(d) applying a force to the metal retainer to simultaneously pull the shank tight and compress the metal retainer axially within the corresponding cavity of the disc and the blade.