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US 12,618,416 B1Granted
Trunnions having multiple fan blades for use with an aircraft engine
OwnerNicholas Joseph Kray, Syed Arif Khalid +1inventors
InventorsNicholas Joseph Kray, Syed Arif Khalid, Arthur W. Sibbach
Life of this patent
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Abstract
Trunnions having multiple fan blades for use with an aircraft engine are disclosed herein. An example comprises a trunnion rotatable within a hub of an aircraft engine, a first fan blade coupled to the trunnion, the first fan blade having a pitch axis, and a second fan blade coupled to the trunnion, the second fan blade having a longitudinal axis, the longitudinal axis laterally offset from the pitch axis.
Claims17
An apparatus comprising:
- a trunnion rotatably mounted within a hub of an aircraft engine, the trunnion having a pitch axis;
- a first fan blade coupled to the trunnion, the first fan blade aligned with the pitch axis of the trunnion;
- a second fan blade coupled to the trunnion, the second fan blade circumferentially offset from the first fan blade and having a longitudinal axis, the longitudinal axis laterally offset from the pitch axis;
- and
- a third fan blade coupled to the trunnion, the third fan blade having a third pitch axis laterally offset from the pitch axis,
- wherein the first fan blade is positioned between the second fan blade and the third fan blade,
- the first fan blade and the second fan blade rotatable with the trunnion with respect to a centerline of the aircraft engine.
4 more elements
An aircraft engine comprising:
- a rotatable trunnion having a pitch axis;
- a first fan blade mounted to the rotatable trunnion, the first fan blade aligned with the pitch axis of the trunnion;
- a second fan blade mounted to the rotatable trunnion, the second fan blade circumferentially offset from the first fan blade and having a longitudinal axis, the longitudinal axis laterally offset from the pitch axis;
- and
- a third fan blade mounted to the rotatable trunnion, the third fan blade having a third pitch axis laterally offset from the pitch axis,
- wherein the first fan blade is positioned between the second fan blade and the third fan blade,
- the first fan blade and the second fan blade rotatable with the rotatable trunnion with respect to a centerline of the aircraft engine.
4 more elements
An aircraft engine comprising:
- a hub;
- a trunnion rotatably coupled to the hub, the trunnion having a pitch axis;
- a first fan blade extending radially away from the hub, the first fan blade having a first base coupled to the trunnion, the first fan blade aligned with the pitch axis of the trunnion;
- a second fan blade extending radially away from the hub, the second fan blade having a second base coupled to the trunnion, the second fan blade circumferentially offset from the first fan blade and having a longitudinal axis, the longitudinal axis laterally offset from the pitch axis;
- and
- a third fan blade coupled to the trunnion, the third fan blade having a third pitch axis laterally offset from the pitch axis,
- wherein the first fan blade is positioned between the second fan blade and the third fan blade,
- the first fan blade and the second fan blade rotatable with the trunnion with respect to a centerline of the aircraft engine.
5 more elements
Dependencies are inferred from the claim text.