Aircraft nacelles having adjustable chines

Patent metadata

Field	Value
Publication number	US-11613345-B2
Application number	US-201916417039-A
Country	US
Kind code	B2
Filing date	May 20, 2019
Priority date	May 20, 2019
Publication date	Mar 28, 2023
Grant date	Mar 28, 2023

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 translatable relative to the nacelle along the fore-aft direction.

First claim

What is claimed is:

1. An apparatus, comprising:
a nacelle of an aircraft engine, the nacelle including an outer surface and a slot formed in the outer surface, the slot oriented along a fore-aft direction of the nacelle, the slot including a front end and a rear end located opposite the front end; and
a chine located on the nacelle, the chine including an outer mold line having a leading edge and a trailing edge located opposite the leading edge, the chine translatable within the slot along the fore-aft direction between a forward position and a rearward position, the outer mold line extending radially outward from the outer surface when the chine is in the forward position, wherein the leading edge is adjacent the front end when the chine is in the forward position and spaced rearward of the front end when the chine is in the rearward position, and wherein the trailing edge is spaced forward of the rear end when the chine is in the forward position and adjacent the rear end when the chine is in the rearward position,
wherein the forward position is a deployed position of the chine and the rearward position is a stowed position of the chine,
wherein a portion of the chine extends outwardly from the outer surface of the nacelle when the chine is in the deployed position, and the portion of the chine is retracted inwardlyfrom the outer surface of the nacelle when the chine is in the stowed position.

2. The apparatus of claim 1 , wherein the fore-aft direction is substantially parallel to a central axis of the nacelle.

3. The apparatus of claim 1 , 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 forward position; and
generate a second vortex when the chine is in the rearward position, the second vortex differing from the first vortex.

4. The apparatus of claim 1 , further comprising:
an actuation mechanism operatively coupled to the chine, the actuation mechanism configured to translate the chine within the slot along the fore-aft direction; and
a controller operatively coupled to the actuation mechanism, the controller configured to control the actuation mechanism.

5. The apparatus of claim 4 , wherein the controller is configured to command the actuation mechanism to translate the chine within the slot in response to the controller detecting at least one of a first threshold parameter associated with an angle of attack of an aircraft to which the nacelle is coupled, a second threshold parameter associated with a leading edge device of a wing of the aircraft, a third threshold parameter associated with a trailing edge device of the wing, a fourth threshold parameter associated with an attitude of the aircraft, a fifth threshold parameter associated with an altitude of the aircraft, a sixth threshold parameter associated with an airspeed of the aircraft, or a seventh threshold parameter associated with a Mach number of the aircraft.

6. The apparatus of claim 1 , wherein the outer mold line of the chine extends radially outward from the outer surface when the chine is in the rearward position.

7. The apparatus of claim 1 , further comprising a wing, wherein the nacelle is coupled to the wing via a pylon extending downward from the wing.

8. The apparatus of claim 7 , wherein a leading edge of the nacelle and the leading edge of the chine are located forward of and below a leading edge of the wing when the chine is in the forward position.

9. The apparatus of claim 1 , wherein the outer mold line of the chine tapers toward the outer surface of the nacelle from the trailing edge of the chine toward the leading edge of the chine.

10. The apparatus of claim 1 , wherein the chine has a planar shape defined by the outer mold line.

11. The apparatus of claim 1 , wherein the chine is located on the nacelle inboard of a central axis of the nacelle.

12. A method, comprising:
translating a chine located on a nacelle of an aircraft engine, the nacelle including an outer surface and a slot formed in the outer surface, the slot oriented along a fore-aft direction of the nacelle, the slot including a front end and a rear end located opposite the front end, the chine including an outer mold line having a leading edge and a trailing edge located opposite the leading edge, the chine translatable within the slot along the fore-aft direction between a forward position and a rearward position, the outer mold line extending radially outward from the outer surface when the chine is in the forward position, wherein the leading edge is adjacent the front end when the chine is in the forward position and spaced rearward of the front end when the chine is in the rearward position, and wherein the trailing edge is spaced forward of the rear end when the chine is in the forward position and adjacent the rear end when the chine is in the rearward position,
wherein the forward position is a deployed position of the chine and the rearward position is a stowed position of the chine,
wherein a portion of the chine extends outwardly from the outer surface of the nacelle when the chine is in the deployed position, and the portion of the chine is retracted inwardlyfrom the outer surface of the nacelle when the chine is in the stowed position.

13. The method of claim 12 , wherein the fore-aft direction is substantially parallel to a central axis of the nacelle.

14. The method of claim 12 , further comprising, in response to an airflow presented at the chine:
generating a first vortex via the chine when the chine is in the forward position; and
generating a second vortex via the chine when the chine is in the rearward position, the second vortex differing from the first vortex.

15. The method of claim 12 , further comprising:
controlling an actuation mechanism via a controller operatively coupled to the actuation mechanism, the actuation mechanism operatively coupled to the chine, the actuation mechanism configured to translate the chine within the slot along the fore-aft direction.

16. The method of claim 15 , wherein controlling the actuation mechanism includes commanding the actuation mechanism, via the controller, to translate the chine within the slot in response to the controller detecting at least one of a first threshold parameter associated with an angle of attack of an aircraft to which the nacelle is coupled, a second threshold parameter associated with a leading edge device of a wing of the aircraft, a third threshold parameter associated with a trailing edge device of the wing, a fourth threshold parameter associated with an attitude of the aircraft, a fifth threshold parameter associated with an altitude of the aircraft, a sixth threshold parameter associated with an airspeed of the aircraft, or a seventh threshold parameter associated with a Mach number of the aircraft.

Assignees

• Boeing Co

Inventors

• Philipp Paul Brian
• Konings Christopher Andrew

Classifications

• B64C7/02

  Nacelles · CPC title

• B64C9/36 Primary

  the members being fuselages or nacelles · CPC title

• Y02T50/10

  Drag reduction · CPC title

• B64D29/02 Primary

  associated with wings · CPC title

• B64C23/06 Primary

  by generating vortices · CPC title