Boundary layer ingesting fan
AssigneeUnited Technologies Corporation
InventorSteven H. Zysman
Life of this patent
Estimating the term…
Abstract
A fan assembly for gas turbine engine according to an exemplary embodiment of this disclosure includes, among other possible things, a plurality of fan blades rotatable about a fan rotation axis, each of the plurality of fan blades movable about an axis transverse to the fan rotation axis, a fan nacelle partially surrounding the plurality of fan blades, and a pitch mechanism coupled to the plurality of blades that changes an angle of pitch for each of the plurality of blades corresponding to a circumferential position of the fan blade about the fan rotation axis.
Claims18
A fan assembly for gas turbine engine comprising;
- a plurality of fan blades rotatable about a fan rotation axis, each of the plurality of fan blades movable about an axis transverse to the fan rotation axis;
- a fan nacelle partially surrounding the plurality of fan blades;
- a pitch mechanism coupled to the plurality of blades that changes an angle of pitch for each of the plurality of blades corresponding to a circumferential position of the fan blade about the fan rotation axis.
A gas turbine engine comprising:
- a fan section including a plurality of fan blades rotatable about an axis of rotation;
- a fan nacelle surrounding a portion of the plurality of fan blades;
- a pitch mechanism coupled to each of the plurality of fan blades that changes a pitch angle for each of the plurality of fan blades individually corresponding to ingested airflow velocity corresponding to a circumferential region of fan section.
A method of operating a gas turbine engine mounted within an aircraft fuselage, the method comprising:
- changing a pitch angle for each of a plurality of fan blades rotating into a low airflow velocity region during rotation about a rotational axis;
- and
- changing the pitch angle for each of the plurality of fan blades rotating into a higher airflow velocity region during rotation about rotational axis.
Dependencies are inferred from the claim text.