Patent ID: 7891952

Claim:
A method for fabricating a rotor assembly for a gas turbine engine having a compressor section and a turbine section, the rotor assembly having a central rotational axis, said method comprising: forging a plurality of rotor disk stages separately from one another, wherein at least one of the disk stages is forged from a first material that is configured to withstand a first maximum operating temperature, wherein the disk stages are part of the turbine section of the gas turbine engine; forging a rim separately from the disk stages, the rim forged from a second material that is configured to withstand a second maximum operating temperature that is greater than the first maximum operating temperature; and coupling each disk stage to the rim at an axial-circumferential plane that is obliquely oriented with respect to the central rotational axis such that the disk stages are radially inward of the rim with the rim spanning the disk stages.