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US 11,591,097 B2Granted
Aircraft nacelles having adjustable chines
AssigneeThe Boeing Company
InventorsPaul Brian Philipp, C. Byram Bays-Muchmore, Daniel Joseph Goering
Life of this patent
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Abstract
Aircraft nacelles having adjustable chines are described. An example apparatus includes a chine coupled to a nacelle. The chine is oriented along a fore-aft direction. The chine is rotatable relative to the nacelle about an axis of rotation. The axis of rotation is substantially perpendicular to a plane of the chine defined by an outer mold line of the chine.
Claims21
An apparatus, comprising:
- a wing;
- a nacelle of an aircraft engine, the nacelle coupled to the wing via a pylon extending downward from the wing, the nacelle including an outer surface and a slot formed in the outer surface, the slot having a front end and a rear end located opposite the front end, the slot oriented along a fore-aft direction;
- and
- a chine coupled to and located on the nacelle inboard of a central axis of the nacelle, the chine oriented along the fore-aft direction, the chine positioned within the slot, the chine rotatable within the slot between a first position and a second position relative to the nacelle about an axis of rotation located rearward of the front end of the slot, the axis of rotation substantially perpendicular to a plane of the chine defined by an outer mold line of the chine, the outer mold line of the chine extending radially outward from the outer surface of the nacelle when the chine is in the first position;
- wherein, in response to an airflow presented at the chine, the chine is configured to:
- generate a first vortex when the chine is in the first position, the first vortex impacting a boundary layer at a first location on an upper surface of the wing, the first vortex having a first strength;
- and
- generate a second vortex when the chine is in the second position, the second vortex impacting the boundary layer at a second location on the upper surface of the wing, the second vortex having a second strength, at least one of the second location or the second strength differing from a corresponding one of the first location or the first strength.
5 more elements
A method, comprising:
- rotating a chine coupled to and located on a nacelle of an aircraft engine, the nacelle coupled to a wing via a pylon extending downward from the wing, the chine located inboard of a central axis of the nacelle, the nacelle including an outer surface and a slot formed in the outer surface, the slot having a front end and a rear end located opposite the front end, the slot oriented along a fore-aft direction, the chine oriented along the fore-aft direction and positioned within the slot, the chine rotatable within the slot between a first position and a second position relative to the nacelle about an axis of rotation located rearward of the front end of the slot, the axis of rotation substantially perpendicular to a plane of the chine defined by an outer mold line of the chine, the outer mold line of the chine extending radially outward from the outer surface of the nacelle when the chine is in the first position;
- and
- in response to an airflow presented at the chine:
- generating a first vortex when the chine is in the first position, the first vortex impacting a boundary layer at a first location on an upper surface of the wing, the first vortex having a first strength;
- and
- generating a second vortex when the chine is in the second position, the second vortex impacting the boundary layer at a second location on the upper surface of the wing, the second vortex having a second strength, at least one of the second location or the second strength differing from a corresponding one of the first location or the first strength.
3 more elements
Dependencies are inferred from the claim text.