WING LEADING EDGE HAVING VORTEX GENERATORS

• US 20090020652A1
• Filed: 07/20/2007
• Published: 01/22/2009
• Est. Priority Date: 07/20/2007
• Status: Active Grant

• Current Assignee: Textron Innovations Incorporated (Textron Inc)
• Original Assignee: Cessna Aircraft Company (Textron Inc)
• Inventors: Cleveland, Kenton A., Rincker, Gregory A., Hammer, James L.
• Granted Patent: US 7,900,871 B2
• Time in Patent Office: Days
• US Class Current: 244/204
• CPC Class Codes: B64C 23/06 by generating vortices
• CPC Class Codes: Y02T 50/10 Drag reduction

Abstract

An arrangement of devices as well as a method for improving the aerodynamics of an aircraft wing are disclosed. In embodiments, a plurality of vortex generators are attached in span-wise alignment on an deice boot along the wing'"'"'s leading edge. The vortex generators are, in embodiments, constructed of a flexible material such that they are able to be expanded along with the boot during inflation and deflation thus mechanically involving the aerodynamic devices in the ice-shedding process.

Claims

1. An aircraft wing, comprising:

an deice boot; and

a protrusion on said deice boot, said protrusion being adapted to minimize flow separation.

2. The wing of claim 1 wherein said protrusion has a ramped upper face and two laterally converging sides.

3. The wing of claim 1 wherein said protrusion is a vortex generator.

4. The wing of claim 1 wherein said deice boot includes a plurality of air tubes which extend in a span-wise direction.

5. The wing of claim 1 wherein said deice boot includes a plurality of protruding aerodynamic devices, one of said devices being said protrusion.

6. The wing of claim 1 wherein said protrusion is comprised of a flexible material which is able to flex along with said boot during operation.

7. The wing of claim 1 wherein said protrusion is a vortex generator which has a ramped upper face and two laterally converging sides and said vortex generator is constructed of a flexible material which is able to flex with said boot during operation.

8. The wing of claim 1 wherein said protrusion:

(i) conforms to an outer surface of the leading edge;

(ii) overlaps a forward most point of the wing leading edge;

(iii) has an upwardly ramped upper face; and

(iv) laterally converges from forward edge to a rear end.

9. The wing of claim 8 wherein said protrusion has a pair of laterally converging sides which terminate at a rear edge, said rear edge being substantially normal to the leading edge surface.

10. The wing of claim 8 wherein said protrusion, when viewed in cross section, is fixed to said leading edge such that it overlaps but is clocked slightly backward from said forward-most point of said leading edge.

11. An aerodynamic device, said device comprising:

a ramped upper face and two laterally converging sides; and

said device is adapted such that it is able to be fixed onto and mechanically operational along with an deice boot on a leading edge of an aircraft wing.

12. The device of claim 11 wherein said device is adapted to generate vortices.

13. A plurality of the aerodynamic devices of claim 11 disposed span-wise on said deice boot.

14. The plurality of aerodynamic devices of claim 13 wherein each device in said plurality (i) longitudinally conforms with a surface of said leading edge;

(ii) overlaps a forward-most point of the wing leading edge; and

(iii) diverges from front to rear.

15. The plurality of aerodynamic devices of claim 14 wherein each device in said plurality, when viewed in cross section, is fixed to said leading edge such that it is clocked slightly backward from said forward-most point of said leading edge.

16. The device of claim 11 comprised of flexible neoprene material.

17. A method of improving the aerodynamics of an aircraft wing, said method comprising:

providing a flexible inflatable member;

installing said flexible inflatable member along the leading edge of an aircraft for the purpose of preventing ice buildup by inflating and deflating said member; and

attaching one or more aerodynamic devices to said inflatable member for the purpose of generating vortices.

18. The method of claim 17 comprising:

constructing said one or more aerodynamic devices of a flexible material such that said devices are able to flex along with said inflatable member.

19. The method of claim 18 comprising:

selecting a plurality of vortex generators to serve as said at least one aerodynamic devices.

20. The method of claim 17 comprising:

adapting said devices such that they minimize flow separation when the aircraft approaches a stall.