Patent ID: 10030519

Abstract:
A gas turbine engine is provided. The engine has an axis and a plurality of coaxial turbine discs, including a first disc and a second disc. A face of the first disc is disposed opposite to a face of the second disc. The engine also has a cover plate coaxial with the axis covering the second disc. The second disc includes an arrangement of turbine blade inserts positioned around its periphery. This arrangement is concentric with the plurality of turbine discs. Turbine blade inserts are retained on the second disc at least in part by the cover plate. The engine further comprises a coaxial tie bolt extending through the plurality of coaxial turbine discs, a spanner nut on the end of the tie bold, an arm coaxial with the axis extending from the face of the second disc having a distal end an axial stop extending from the face of the first disc. The distal end is in contact with the axial stop. The axial stop retains the axial movement of the second disc. The cover plate extends axially between the axial stop and the second disc and radially between the arm and the periphery of the second disc.