Turbine engine tip clearance control system with thrust bearing
An assembly is provided for an aircraft powerplant. This assembly includes a rotating assembly, a first structure, a second structure and a thrust bearing. The rotating assembly includes a first bladed rotor and a second bladed rotor. The first bladed rotor includes a plurality of first rotor blades. The second bladed rotor includes a plurality of second rotor blades. The first structure is configured as or otherwise includes a first shroud. The first shroud circumscribes the first bladed rotor. The first shroud is adjacent first tips of the first rotor blades. The second structure is configured as or otherwise includes a second shroud. The second shroud circumscribes the second bladed rotor. The second shroud is adjacent second tips of the second rotor blades. The second shroud is configured to move along an axis relative to the first shroud. The thrust bearing couples the rotating assembly to the second structure.
1. An assembly for an aircraft powerplant, comprising:
a rotating assembly rotatable about an axis, the rotating assembly including a first bladed rotor and a second bladed rotor, the first bladed rotor including a plurality of first rotor blades arranged circumferentially around the axis, and the second bladed rotor including a plurality of second rotor blades arranged circumferentially around the axis;
a first structure comprising a first shroud, the first shroud circumscribing the first bladed rotor, and the first shroud adjacent first tips of the plurality of first rotor blades;
a second structure comprising a second shroud, the second shroud circumscribing the second bladed rotor, the second shroud adjacent second tips of the plurality of second rotor blades, and the second shroud configured to move along the axis relative to the first shroud;
a thrust bearing coupling the rotating assembly to the second structure;
a shaft rotatable about the axis, the shaft extending axially in a bore of the rotating assembly; and
a second bearing radially between and coupling the shaft and the rotating assembly, the second bearing axially aligned with the thrust bearing.
2. The assembly of claim 1 , wherein the first bladed rotor comprises an axial flow rotor.
3. The assembly of claim 1 , wherein the second bladed rotor comprises a radial flow rotor.
4. The assembly of claim 1 , further comprising:
a compressor section;
the first bladed rotor and the second bladed rotor included in adjacent stages of the compressor section.
5. The assembly of claim 1 , wherein
the first shroud and the second shroud each form a respective portion of an outer peripheral boundary of a flowpath which extends across the first bladed rotor and the second bladed rotor; and
the second bladed rotor is downstream of the first bladed rotor along the flowpath.
6. The assembly of claim 1 , wherein the first structure axially interfaces with the second structure at a sliding joint.
7. The assembly of claim 1 , wherein
the second structure further comprises a vane array structure adjacent the second bladed rotor;
an outer platform of the vane array structure is rigidly connected to the second shroud; and
an inner platform of the vane array structure is rigidly connected to the thrust bearing.
8. The assembly of claim 1 , further comprising a flex coupling flexibly coupling the first structure to the second structure.
9. The assembly of claim 1 , wherein
an annular channel projects radially into the rotating assembly towards the axis; and
the thrust bearing is arranged in the annular channel.
10. The assembly of claim 1 , wherein the thrust bearing is arranged axially between and next to the first bladed rotor and the second bladed rotor.
11. The assembly of claim 1 , wherein the thrust bearing is configured to synchronize axial movement of the second bladed rotor along the axis with axial movement of the second shroud along the axis.
12. The assembly of claim 1 , wherein the thrust bearing comprises a foil bearing.
13. The assembly of claim 1 , further comprising:
an engine core including a compressor section, a combustor section and a turbine section; and
a flowpath extending through the compressor section, the combustor section and the turbine section from an inlet into the flowpath to an exhaust from the flowpath, and the flowpath further extending across the first bladed rotor and the second bladed rotor.
14. The assembly of claim 1 , further comprising:
a mechanical load; and
a powerplant engine configured to power the mechanical load, the powerplant engine including the rotating assembly, the first structure and the second structure.
15. The assembly of claim 14 , further comprising:
a power turbine section configured to drive rotation of a propulsor rotor;
the mechanical load comprising the propulsor rotor.