US 12,421,863 B2
Turbine engine tip clearance control system with thrust bearing
Andrew E. Breault, Bolton, CT (US); and Jeffrey T. Morton, Manchester, CT (US)
Assigned to RTX CORPORATION, Farmington, CT (US)
Filed by Raytheon Technologies Corporation, Farmington, CT (US)
Filed on Jul. 21, 2023, as Appl. No. 18/224,934.
Prior Publication US 2025/0027423 A1, Jan. 23, 2025
Int. Cl. F01D 11/14 (2006.01); F01D 25/16 (2006.01)
CPC F01D 11/14 (2013.01) [F01D 25/16 (2013.01); F05D 2240/52 (2013.01)] 15 Claims
OG exemplary drawing
 
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.