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US 2016/0146025 A1Published application
Variable pitch fan for gas turbine engine and method of assembling the same
AssigneeGeneral Electric Company
InventorsBrandon Wayne Miller, Ian Francis Prentice, Daniel Alan Niergarth
Life of this patent
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Abstract
A gas turbine engine is provided. The gas turbine engine includes a core and a variable pitch fan arranged in flow communication with the core. The variable pitch fan has a disk and at least nine fan blades coupled to the disk for rotation together with the disk. The gas turbine engine further includes a rotatable nacelle covering the disk such that the engine has a fan hub radius ratio of between about 0.1 and about 0.4.
Claims20
A gas turbine engine comprising:
- a core;
- a variable pitch fan arranged in flow communication with said core, said variable pitch fan comprising a disk and at least nine fan blades coupled to said disk for rotation together with said disk;
- and
- a rotatable nacelle covering said disk such that said engine has a fan hub radius ratio of between about 0.1 and about 0.4.
1 more element
A method of assembling a gas turbine engine, said method comprising:
- providing a core;
- coupling a variable pitch fan to a turbine that is configured to be powered by combustion gas from the core, the variable pitch fan including a disk and at least nine fan blades coupled to the disk for rotation together with the disk;
- and
- covering the disk with a rotatable nacelle such that the engine has a fan hub radius ratio of between about 0.1 and about 0.4.
1 more element
A gas turbine engine comprising:
- a core;
- a variable pitch fan arranged in flow communication with said core, said variable pitch fan comprising a disk and at least nine fan blades each coupled to said disk via a trunnion mechanism for rotation together with said disk, said trunnion mechanism comprising a pair of line contact bearings;
- an actuation mechanism for varying a pitch of said fan blades;
- one of a remote counterweight device and a remote pitch lock device operatively coupled to said fan blades via said actuation mechanism;
- a plurality of outlet guide vanes aft of said fan;
- and
- a rotatable nacelle covering said disk such that said engine has a fan hub radius ratio of between about 0.1 and about 0.4.
4 more elements
Dependencies are inferred from the claim text.