Crushable bearing ring for a fan assembly
AssigneeGeneral Electric Company
InventorsNicholas Joseph Kray, Daniel Edward Mollmann, Nicholas M. Daggett, Arthur William Sibbach
Life of this patent
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Abstract
A gas turbine engine is provided. The gas turbine engine includes: a fan blade and a trunnion. The trunnion defines a longitudinal direction and a transverse direction. The fan blade is coupled to the trunnion. The gas turbine engine further includes a disk. The trunnion is coupled to the disk and defines a load path from the trunnion to the disk. The gas turbine engine further includes a crushable bearing ring positioned between the trunnion and the disk along the defined load path.
Claims20
A gas turbine engine comprising:
- a fan blade;
- a trunnion defining a longitudinal direction and a transverse direction, the fan blade coupled to the trunnion;
- a disk, the trunnion coupled to the disk and defining a load path from the trunnion to the disk;
- a bearing positioned between the trunnion and the disk;
- and
- a crushable bearing ring positioned outward of the bearing along the transverse direction between the trunnion and the disk along the load path.
A connection assembly for a variable pitch fan assembly of a gas turbine engine, the connection assembly comprising:
- a trunnion defining a longitudinal direction and a transverse direction;
- a disk, the trunnion and disk defining a load path;
- a first bearing positioned between the trunnion and the disk;
- a first crushable bearing ring located along the load path between the disk and the trunnion and positioned outward of the bearing along the transverse direction;
- and
- a second crushable bearing ring along the load path, the second crushable bearing ring spaced from the first crushable bearing ring along the longitudinal direction.
Dependencies are inferred from the claim text.