Balanced rotor for a gas turbine engine.

摘要

A balanced rotor (21) for a gas turbine engine (10) comprises a disc (22) which carries an annular array of aerofoil blades (23). Each of said aerofoil blades (23) has a fir-tree root portion (27) which locates in a corresponding groove (28) in the disc (22). The blade root portions (27) are retained axially by retention plates (29) located in an annular array on the rotor (21) adjacent the root portions (27). A minority of the retention plates (29) are lighter than the remainder. The lighter plates (29) are so distributed around the rotor as to ensure the balance of the rotor (21).