COMPRESSOR-TURBINE ROTATING ASSEMBLY WITH INTEGRAL COOLING CIRCUIT(S)

An assembly (58) for a gas turbine engine (20) includes a compressor rotor (38), a turbine rotor (40) and a cooling circuit (60). The compressor rotor (38) includes a gas path surface (68). The turbine rotor (40) is rotatable with the compressor rotor (38) about a rotational axis. The cooling circuit (60) includes an inlet (102) in the gas path surface (68). The cooling circuit (60) extends from the inlet (102), through the compressor rotor (38) and into the turbine rotor (40).