Axial compressor rotor assembly

A compressor rotor assembly for a gas turbine engine, comprising:

• a compressor section including an upstream end and a downstream end;
• a forward bearing assembly at the upstream end;
• a rearward bearing assembly at the downstream end;
• a plurality of rotor stages extending axially along and circumferentially about an axial centerline between the upstream end and the downstream end, each of the plurality of rotor stages extending radially between an inner radial hub and an outer radial rim, each of the plurality of rotor stages including an airfoil extending spanwise from the outer radial rim to a tip, the plurality of rotor stages comprising a first rotor stage and a second rotor stage, the first rotor stage disposed forward the second rotor stage, the second rotor stage including an interstage shaft;
• the interstage shaft including an outer radial end and an inner radial end, the interstage shaft extending axially between the first rotor stage and the second rotor stage, the outer radial end extending axially from an upstream end of the second rotor stage, the interstage shaft tapering radially inward from the outer radial end to the inner radial end, the interstage shaft including an arm extending axially from the interstage shaft as the interstage shaft tapers radially inward towards the inner radial end, the arm extending axially towards the downstream end of the first rotor stage, and the first rotor stage attached to the arm;
• wherein a stack load path of the compressor rotor assembly is directed into the interstage shaft and away from the first rotor stage.