CPC F16C 27/04 (2013.01) [F01D 25/164 (2013.01); F16C 35/077 (2013.01); F16C 2360/23 (2013.01)] | 17 Claims |
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.
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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.
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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.
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