Variable pitch fan actuator

Patent metadata

Field	Value
Publication number	US-11085310-B2
Application number	US-201816188373-A
Country	US
Kind code	B2
Filing date	Nov 13, 2018
Priority date	Nov 17, 2015
Publication date	Aug 10, 2021
Grant date	Aug 10, 2021

Abstract

A gas turbine engine including a core having in serial flow order a compressor, a combustor, and a turbine—the compressor, combustor, and turbine together defining a core air flowpath. The gas turbine engine additionally includes a fan section mechanically coupled to the core, the fan section including a plurality of fan blades, and each of the plurality fan blades defining a pitch axis. An actuation device is operable with the plurality fan blades for rotating the plurality fan blades about their respective pitch axes, the actuation device including an actuator located outward of the core air flowpath to, e.g., simplify the gas turbine engine.

First claim

What is claimed is:

1. An actuation device for a gas turbine engine, the gas turbine engine comprising a core and a fan section mechanically coupled to the core, the core defining a core air flowpath, the fan section comprising a plurality of fan blades each rotatable about a pitch axis, the actuation device defining a central axis and comprising:
an actuator configured for installation in the gas turbine engine and for rotating the plurality of fan blades; and
a connection assembly coupled to the actuator and configured for operably connecting the actuator to the plurality of fan blades, the connection assembly comprising a multi-jointed coupling and a rotating to static transfer device, the multi-jointed coupling comprising multiple non-linear joints and extending between the actuator and the rotating to static transfer device to provide a non-linear connection between the actuator and the rotating to static transfer device, wherein a first non-linear joint of the multiple non-linear joints is positioned closer in proximity to the actuator than any other non-linear joint of the multiple non-linear joints, a second non-linear joint of the multiple non-linear joints is positioned closer in proximity to the rotating to static transfer device than any other non-linear joint of the multiple non-linear joints, and the first non-linear joint is positioned farther from the central axis, in a radial direction perpendicular to the central axis, than the second non-linear joint.

2. The actuation device of claim 1 , wherein said rotating to static transfer device of said connection assembly is configured to be positioned in the fan section of the gas turbine engine when said actuation device is installed within the gas turbine engine.

3. The actuation device of claim 1 , wherein said rotating to static transfer device comprises an inner race, an outer race, and a plurality of bearings located between said inner race and said outer race.

4. The actuation device of claim 1 , wherein the multi-jointed coupling-comprises a non-rotating mechanical coupling extending between said rotating to static transfer device and said actuator.

5. The actuation device of claim 4 , wherein said non-rotating mechanical coupling comprises a plurality of connection rods.

6. The actuation device of claim 4 , wherein the actuator is a linear actuator.

7. The actuation device of claim 1 , wherein said connection assembly further comprises a rotating mechanical coupling extending from said rotating to static transfer device, wherein said rotating mechanical coupling is configured to rotate at least one of the plurality of fan blades about the respective pitch axis of the at least one of the plurality of fan blades.

8. The actuation device of claim 1 , wherein the core further comprises a strut extending through the core air flowpath, and wherein the connection assembly is configured to extend through the strut.

Assignees

• Gen Electric

Inventors

• Niergarth Daniel Alan
• Zatorski Darek Tomasz
• Miller Brandon Wayne

Classifications

• F05D2220/36

  specially adapted for the fan of turbofan engines · CPC title

• F05D2260/76

  the adjusting mechanism using auxiliary power sources · CPC title

• F05B2220/302

  in gas turbines · CPC title

• F05D2260/70

  Adjusting of angle of incidence or attack of rotating blades · CPC title

• Y02T50/60

  Efficient propulsion technologies, e.g. for aircraft · CPC title