Integrated slat chine apparatus and methods

Patent metadata

Field	Value
Publication number	US-10618625-B2
Application number	US-201715648103-A
Country	US
Kind code	B2
Filing date	Jul 12, 2017
Priority date	Jul 12, 2017
Publication date	Apr 14, 2020
Grant date	Apr 14, 2020

Abstract

Integrated slat chine apparatus and methods are described. An example apparatus includes a chine and a slat. The chine is coupled to an airfoil. The chine includes a lateral surface. The slat is located adjacent the lateral surface of the chine and coupled to the airfoil. The slat is movable relative to the airfoil between a stowed position and a deployed position. The slat is to expose the lateral surface of the chine when the slat is in the deployed position and to cover the lateral surface of the chine when the slat is in the stowed position.

First claim

What is claimed is:

1. An apparatus, comprising:
a chine coupled to an airfoil at a fixed position relative to a leading edge of the airfoil, the chine having a lateral surface; and
a slat located adjacent the lateral surface of the chine and coupled to the airfoil, the slat being movable relative to the airfoil between a stowed position and a deployed position, the slat exposing the lateral surface of the chine when the slat is in the deployed position, the slat completely covering the lateral surface of the chine when the slat is in the stowed position.

2. The apparatus of claim 1 , wherein the chine is located at the leading edge of the airfoil.

3. The apparatus of claim 2 , wherein the chine extends from the leading edge of the airfoil in a first direction that is parallel to a second direction, the slat being moveable relative to the airfoil along the second direction.

4. The apparatus of claim 1 , wherein the chine is located outboard of a nacelle coupled to the airfoil.

5. The apparatus of claim 1 , wherein a portion of an outer mold line of the slat is flush with a portion of an outer mold line of the chine when the slat is in the stowed position.

6. The apparatus of claim 1 , wherein the chine generates a vortex to energize a boundary layer of the airfoil in response to an airflow presented at the chine when the slat is in the deployed position, and wherein the chine does not generate the vortex when the slat is in the stowed position.

7. The apparatus of claim 1 , wherein the lateral surface of the chine is a first lateral surface of the chine located opposite a second lateral surface of the chine, the slat is a first slat located adjacent the first lateral surface of the chine, the stowed position is a first stowed position, and the deployed position is a first deployed position, the apparatus further comprising a second slat located adjacent the second lateral surface of the chine and coupled to the airfoil, the second slat being movable relative to the airfoil between a second stowed position and a second deployed position, the second slat exposing the second lateral surface of the chine when the second slat is in the second deployed position, the second slat completely covering the second lateral surface of the chine when the second slat is in the second stowed position.

8. An apparatus, comprising:
a chine coupled to an airfoil at a fixed position relative to a leading edge of the airfoil, the chine having a first lateral surface and a second lateral surface located opposite the first lateral surface; and
a slat coupled to the airfoil, the chine being located within a lateral extent of the slat along a spanwise direction of the airfoil, the slat being movable relative to the airfoil between a stowed position and a deployed position, the slat exposing the first lateral surface and the second lateral surface of the chine when the slat is in the deployed position, the slat covering the first lateral surface and the second lateral surface of the chine when the slat is in the stowed position.

9. The apparatus of claim 8 , wherein the chine is located at the leading edge of the airfoil.

10. The apparatus of claim 9 , wherein the chine extends from the leading edge of the airfoil in a first direction that is parallel to a second direction, the slat being moveable relative to the airfoil along the second direction.

11. The apparatus of claim 8 , wherein the chine is located outboard of a nacelle coupled to the airfoil.

12. The apparatus of claim 8 , wherein a portion of an outer mold line of the slat is flush with a portion of an outer mold line of the chine when the slat is in the stowed position.

13. The apparatus of claim 8 , wherein the chine generates a vortex to energize a boundary layer of the airfoil in response to an airflow presented at the chine when the slat is in the deployed position, and wherein the chine does not generate the vortex when the slat is in the stowed position.

14. An apparatus, comprising:
a chine coupled to an airfoil at a fixed position relative to a leading edge of the airfoil, the chine having an outer mold line; and
a slat coupled to the airfoil, the chine being located within a lateral extent of the slat along a spanwise direction of the airfoil, the slat being movable relative to the airfoil between a stowed position and a deployed position, the slat exposing the outer mold line of the chine when the slat is in the deployed position, the slat covering the outer mold line of the chine when the slat is in the stowed position.

15. The apparatus of claim 14 , wherein the chine is located at the leading edge of the airfoil.

16. The apparatus of claim 15 , wherein the chine extends from the leading edge of the airfoil in a first direction that is parallel to a second direction, the slat being moveable relative to the airfoil along the second direction.

17. The apparatus of claim 15 , wherein the chine extends from the leading edge of the airfoil in a first direction that is at an angle relative to a second direction, the slat being movable relative to the airfoil along the second direction.

18. The apparatus of claim 17 , wherein the angle is approximately fifteen degrees in an inboard direction.

19. The apparatus of claim 14 , wherein the chine is located outboard of a nacelle coupled to the airfoil.

20. The apparatus of claim 14 , wherein the chine generates a vortex to energize a boundary layer of the airfoil in response to an airflow presented at the chine when the slat is in the deployed position, and wherein the chine does not generate the vortex when the slat is in the stowed position.

Assignees

• Boeing Co

Inventors

• Leopold David Daniel

Classifications

• B64C9/26

  by multiple flaps · CPC title

• B64C9/22

  at the front of the wing · CPC title

• B64C9/34

  collapsing or retracting against or within other surfaces or other members · CPC title

• B64C9/14 Primary

  forming slots · CPC title

• B64C23/06

  by generating vortices · CPC title