Pitch-controlled blade retention collar
AssigneeGeneral Electric Company
InventorsNicholas J. Kray, Arthur W. Sibbach, Shawn P. Riley
Life of this patent
Estimating the term…
Abstract
Collars to retain multiple fan blades for use with an aircraft engine are disclosed herein. An example gas turbine engine includes a plurality of fan blades and a collar coupled to the plurality of fan blades. The collar includes a first mating piece and a second mating piece coupled to the first mating piece. The first and second mating pieces define an opening configured to receive a first root of a first fan blade of the plurality of fan blades, and the first and second mating pieces define a slot to retain a second root of a second fan blade of the plurality of fan blades.
Claims20
A gas turbine engine comprising:
- a plurality of fan blades;
- a collar coupled to the plurality of fan blades;
- and
- a trunnion that includes a first member and a second member, the first member to accept a component of the trunnion, the second member to accept the collar, wherein coupling of the first member and the second member couples the collar and the component.
A trunnion for a gas turbine engine comprising:
- a first member to accept a component of the trunnion;
- and
- a second member to accept a collar for a plurality of fan blades, wherein coupling of the first member and the second member couples the collar and the component.
A blade assembly comprising:
- a plurality of fan blades;
- and
- a trunnion including a first member and a second member, the first member to accept a component of the trunnion, the second member to accept a collar coupled to the plurality of fan blades, wherein coupling of the first member and the second member couples the collar and the component.
Dependencies are inferred from the claim text.