Stiffened torque tube for gas turbine engine

A method of reducing stresses in a gas turbine engine rotor assembly, the method comprising:

• unbolting a disc fastening flange of a first stage turbine rotor disc adapter from a shaft fastening flange of a torque tube;
• attaching a stiffening ring to one or both of the disc fastening flange and the shaft fastening flange;
• and
• re-bolting the disc fastening flange and the shaft fastening flange:
• wherein:
• the gas turbine engine rotor assembly extends along a central longitudinal axis such that the disc fastening flange and the shaft fastening flange each comprise annular bodies surrounding the central longitudinal axis;
• and
• the stiffening ring is located at an inner diameter of one or both of the annular bodies.

A method of reducing stresses in a gas turbine engine rotor assembly, the method comprising:

• unbolting a disc fastening flange of a first stage turbine rotor disc adapter from a shaft fastening flange of a torque tube;
• attaching a stiffening ring to one or both of the disc fastening flange and the shaft fastening flange;
• and
• re-bolting the disc fastening flange and the shaft fastening flange;
• wherein:
• the torque tube comprises a notch at a juncture between a shaft connecting the shaft fastening flange to the torque tube;
• and
• the stiffening ring results in a ratio of a thickness of the shaft at the notch over a thickness of one or both of the shaft fastening flange and disc fastening flange decreasing to below approximately 0.2.