Aircraft blade seal

• US 10,640,196 B1
• Filed: 09/05/2017
• Issued: 05/05/2020
• Est. Priority Date: 09/05/2017
• Status: Active Grant

• Current Assignee: Northrop Grumman Systems Corporation (Northrop Grumman Corporation)
• Original Assignee: Northrop Grumman Systems Corporation (Northrop Grumman Corporation)
• Inventors: Wadolkowski, Krzysztof H., Walker, Maurice E., Soberon, Peter A., Gardner, Daniel S., Nelson, Jacob D., Nelson, Jeremy M.
• Primary Examiner(s): Sanderson, Joseph W
• Application Number:
  US15/695,790
• Time in Patent Office: 973 Days
• CPC Class Codes: B64C 2009/005 Ailerons
• CPC Class Codes: B64C 9/02 Mounting or supporting thereof
• CPC Class Codes: B64C 9/14 forming slots

Abstract

A blade seal for covering an interface between first and second components of an aircraft includes a mounting portion extending in a longitudinal first direction for connection to the first component. A contact portion maintains contact with the second component. A plurality of pockets positioned along the first direction are separated by projections extending in a second direction perpendicular to the length. Each pocket has a variable depth and facing the second component.

Claims

1. A blade seal for covering an interface between first and second components of an aircraft, the blade seal comprising:

a mounting portion extending in a longitudinal first direction for connection to the first component;

a contact portion for maintaining contact with the second component; and

a plurality of pockets positioned along the first direction and separated by projections extending in a second direction perpendicular to the first direction, each pocket having a non-uniform depth and being defined by a non-vertical wall having legs that taper inwards such that a width of each leg in the first direction decreases in the second direction.

2. The blade seal recited in claim 1, wherein the mounting portion is configured for connection the first component comprising an aircraft wing and the contact portion is configured for maintaining contact with the second component comprising an aileron.

3. The blade seal recited in claim 1, wherein the mounting portion is configured for connection the first component comprising an aircraft wing and the contact portion is configured for maintaining contact with the second component comprising a flap.

4. The blade seal recited in claim 1, wherein the projections are trapezoidal.

5. The blade seal recited in claim 1, wherein the projections have a thickness that decreases in the second direction.

6. The blade seal recited in claim 1, wherein the depth of each pocket is defined between first and second surfaces, the wall extending transverse to the first and second surfaces such that the wall faces away from the second surface.

7. The blade seal recited in claim 6, wherein the pockets have a uniform width in the first direction at the second surface.

8. The blade seal recited in claim 1, wherein each of the projections has a width in the first direction that increases along the second direction.

9. The blade seal recited in claim 1, wherein wall is U-shaped, the pair of legs extends in the second direction and a connecting portion extends in the first direction.

10. The blade seal recited in claim 1, wherein the blade seal includes opposing first and second surfaces, the depth of each pocket being defined from the first surface to a third surface between the first and second surfaces and being non-uniform in the second direction.

11. The blade seal recited in claim 1, wherein the projections extend to the mounting portion.

12. The blade seal recited in claim 1, wherein the contact portion elastically deflects relative to the mounting portion in response to relative movement between the first and second components.

13. The blade seal recited in claim 1, wherein all the pockets are exposed.

14. The blade seal recited in claim 1, wherein the depth is along a third direction perpendicular to the first and second directions.

15. The blade seal recited in claim 1, wherein the wall faces the second component.

16. A blade seal for covering an interface between first and second components of an aircraft, the blade seal comprising:

a mounting portion extending in a longitudinal first direction for connection to the first component;

a contact portion for maintaining contact with the second component; and

a plurality of pockets positioned along the first direction and separated by trapezoidal projections extending in a second direction perpendicular to the first direction, each pocket having a non-uniform depth and being defined by a non-vertical wall extending transversely between first and second surfaces of the blade seal, each pocket and each wall facing the second component.

17. The blade seal recited in claim 16, wherein the mounting portion is configured for connection the first component comprising an aircraft wing and the contact portion is configured for maintaining contact with the second component comprising an aileron.

18. The blade seal recited in claim 16, wherein the mounting portion is configured for connection the first component comprising an aircraft wing and the contact portion is configured for maintaining contact with the second component comprising a flap.

19. The blade seal recited in claim 16, wherein the wall is U-shaped and includes a pair of legs extending in the second direction and a connecting portion extending in the first direction.

20. The blade seal recited in claim 16, wherein the projections extend to the mounting portion.

21. The blade seal recited in claim 16, wherein the contact portion elastically deflects relative to the mounting portion in response to relative movement between the first and second components.

22. The blade seal recited in claim 16, wherein all the pockets are exposed.

23. The blade seal recited in claim 16, wherein the pockets have a uniform width in the first direction at the second surface.