Turbine engine tip clearance control system with thrust bearing

An assembly for an aircraft powerplant, comprising:

• a rotating assembly rotatable about an axis and including a bladed rotor, the bladed rotor including a plurality of rotor blades arranged circumferentially around the axis;
• a structure comprising a shroud and a vane array structure, the shroud circumscribing the bladed rotor, the shroud adjacent tips of the plurality of rotor blades, an outer platform of the vane array structure rigidly connected to an upstream end of the shroud;
• and
• a thrust bearing coupling the rotating assembly to the structure, the thrust bearing rigidly connected to an inner platform of the vane array structure.

An assembly for an aircraft powerplant, comprising:

• a rotating assembly rotatable about an axis and including a radial flow compressor rotor, the radial flow compressor rotor including a plurality of compressor blades arranged circumferentially around the axis;
• a structure comprising a shroud, the shroud circumscribing the radial flow compressor rotor, and the shroud adjacent tips of the plurality of compressor blades;
• a thrust bearing coupling the rotating assembly to the structure, the thrust bearing configured to link axial movement of the radial flow compressor rotor along the axis with axial movement of the shroud along the axis;
• a shaft projecting axially through a bore of the rotating assembly;
• and
• a second bearing coupling the shaft to the rotating assembly, the second bearing axially aligned with the thrust bearing along the axis.