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A gas turbine engine includes a compressor rotor assembly which directs air at a sufficent pressure and temperature to a compressor rotor bore. The compressor assembly includes a compressor including a plurality of rotors joined with a plurality of couplings. Each of the rotors includes a radially o

A gas turbine engine includes a compressor rotor assembly which directs air at a sufficent pressure and temperature to a compressor rotor bore. The compressor assembly includes a compressor including a plurality of rotors joined with a plurality of couplings. Each of the rotors includes a radially outer rim, a radially inner hub, and a web extending therebetween. The web includes a flange including a plurality of slots which define a plurality of radial vanes that are airfoil-shaped. The vanes effectively deswirl bleed air and re-direct the airflow to a compressor bore.

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1. A method of fabricating a compressor rotor assembly to supply pressurized airflow to a compressor bore in a gas turbine engine, the rotor assembly including at least one rotor including a radially outer rim, a radially inner hub, and a web extending therebetween, and a plurality of circumferentia

1. A method of fabricating a compressor rotor assembly to supply pressurized airflow to a compressor bore in a gas turbine engine, the rotor assembly including at least one rotor including a radially outer rim, a radially inner hub, and a web extending therebetween, and a plurality of circumferentially spaced apart rotor blades extending radially outwardly from the rim, the web including a deswirler assembly including a flange, said method comprising the steps of:integrating a plurality of slots into the flange; and defining radial vanes within the flange to direct airflow radially inward towards the compressor bore, such that at least one vane defines a curved flowpath.