US 11,674,548 B2
Low profile rotating bearing centering spring
Todd A. Davis, Tolland, CT (US); and Paul R. Hanrahan, Farmington, CT (US)
Assigned to RAYTHEON TECHNOLOGIES CORPORATION, Farmington, CT (US)
Filed by Raytheon Technologies Corporation, Farmington, CT (US)
Filed on Jun. 26, 2020, as Appl. No. 16/913,019.
Prior Publication US 2021/0404480 A1, Dec. 30, 2021
Int. Cl. F16C 27/04 (2006.01); F01D 25/16 (2006.01); F16C 35/077 (2006.01)
CPC F16C 27/04 (2013.01) [F01D 25/164 (2013.01); F16C 35/077 (2013.01); F16C 2360/23 (2013.01)] 17 Claims
OG exemplary drawing
 
1. A bearing assembly of a gas turbine engine, comprising:
a bearing inner race;
a bearing outer race located radially outboard of the bearing inner race;
a plurality of bearing elements located between the bearing inner race and the bearing outer race; and
a centering spring operably connected to and supporting of the bearing outer race, the centering spring being an annular structure including:
a base portion;
a tip portion; and
a plurality of beams extending axially between the base portion and the tip portion;
wherein the bearing outer race and the centering spring are configured to rotate about an engine central longitudinal axis; and
wherein the centering spring includes a first stop at the tip portion to limit radially outward deflection of the centering spring and the bearing outer race connected thereto.
 
7. A shaft assembly of a gas turbine engine, comprising:
a first shaft disposed at and rotatable about an engine central longitudinal axis;
a second shaft concentric with the first shaft; and
a bearing assembly supportive of the second shaft relative to the first shaft, the bearing assembly including:
a bearing inner race disposed at the first shaft;
a bearing outer race located radially outboard of the bearing inner race and disposed at the second shaft;
a plurality of bearing elements located between the bearing inner race and the bearing outer race; and
a centering spring operably connected to and supporting of the bearing outer race, the centering spring being an annular structure including:
a base portion;
a tip portion; and
a plurality of beams extending axially between the base portion and the tip portion
wherein the centering spring includes a first stop at the tip portion to limit radially outward deflection of the centering spring and the bearing outer race connected thereto.
 
13. A gas turbine engine, comprising:
a combustor; and
a turbine section driven by combustion gasses of the combustor, the turbine section including:
a first shaft disposed at and rotatable about an engine central longitudinal axis;
a second shaft concentric with the first shaft; and
a bearing assembly supportive of the second shaft relative to the first shaft, the bearing assembly including:
a bearing inner race disposed at the first shaft;
a bearing outer race located radially outboard of the bearing inner race and disposed at the second shaft;
a plurality of bearing elements located between the bearing inner race and the bearing outer race; and
a centering spring operably connected to and supporting of the bearing outer race, the centering spring being an annular structure including:
a base portion;
a tip portion; and
a plurality of beams extending axially between the base portion and the tip portion;
wherein the centering spring includes a first stop at the tip portion to limit radially outward deflection of the centering spring.