Patent ID: 10718220

Abstract:
In accordance with some embodiments of the present disclosure, a gas turbine engine is presented. The engine has at least one turbine stage and each stage has a turbine disc concentric with the axis of the engine. The turbine disc has a turbine arm positioned axially from the disc and rigidly attached thereto. The drive arm is also concentric with the turbine axis and has an outer surface. The turbine stage also has a cover plate concentric with the turbine axis and covering at least a portion of the turbine disc. An arrangement of turbine blades are positioned around the periphery of the disc and are retained on the turbine disc at least partially by the cover plate. The system includes a spanner nut, and threads on a portion of the turbine drive arm. The spanner nut is threaded onto the turbine arm which applies an axial force on the cover plate, thereby retaining the cover plate.