HEATING SYSTEM

• US 20120085867A1
• Filed: 05/06/2010
• Published: 04/12/2012
• Est. Priority Date: 05/06/2009
• Status: Abandoned Application

• Current Assignee: GKN Aerospace Services Limited (Melrose Industries Plc)
• Original Assignee: GKN Aerospace Services Limited (Melrose Industries Plc)
• Inventors: Bardwell, Anthony Edward
• Application Number:
  US13/318,889
• Publication Number:
  US 20120085867A1
• Time in Patent Office: Days
• US Class Current: 244/134.B
• CPC Class Codes: B64D 15/06 Liquid application in general B05
• CPC Class Codes: B64D 15/12 by electric heating electric heating elements in general H05B

Abstract

A heating system for heating at least a portion of a leading edge (114) of an aircraft wing (112). The system comprising a first portion (5) of a heat pipe (4) positioned between an end of an aircraft wing support rib (6) and a portion of the leading edge (9) proximate to the end of the support rib wherein heat from the heat pipe is transferable to the proximate portion of the leading edge profile.

Claims

1. A heating system for a leading edge of an aircraft wing, said system comprising at least one heat pipe having a first end arranged in use to receive input heat and a second end arranged in use to dissipate heat, wherein said second end of said heat pipe is positioned between an end portion of a wing support rib and an adjacent portion of a wing leading edge.

2. A heating system according to claim 1, further comprising heating means adapted to provide said input heat to said first end of said heat pipe.

3. A heating system according to claim 1, wherein the first end of said heat pipe extends from said second end away from said support rib.

4. A heating system according to claim 2, wherein the heating means is an electrically operated heater and is coupled to said first end of said heat pipe.

5. A heating system according to claim 1, wherein the heat pipe is substantially rectangular in cross-section.

6. A heating system according to claim 1, wherein the heat pipe is substantially circular in cross-section.

7. A heating system according to claim 6, wherein the second end of said heat pipe is arranged to be received in a channel or cavity formed in a portion of said rib proximate to said leading edge.

8. A heating system as claimed in claim 1, wherein at least a part of said heat pipe is provided with curvature corresponding to the curvature of the inner surface of the wing leading edge.

9. A heating system as claimed in claim 1, comprising a plurality of heat pipes extending around at least a portion of an inner surface of a wing leading edge.

10. A heating system according to claim 1, wherein the rib is coupled to the leading edge surface through a plurality of holes extending through a portion of said rib proximate to the leading edge of said wing.

11. A heating system as claimed in claim 10, wherein the heat pipe is/are formed as conduits extending along and between a portion of the interface between the rib and the inner surface of the leading edge and wherein the holes are arranged between adjacent heat pipe conduits.

12. A heating system as claimed in claim 1, wherein the first end of said heat pipe is disposed at an angle relative to the elongate axis defined by the first end of said pipe extending from the rib/leading edge interface.

13. A method of heating a leading edge on an aircraft wing, the steps comprising:

positioning at least a portion of a heat pipe between an end of an aircraft wing support rib and a portion of said leading edge proximate to said end of said support rib; and

heating said heat pipe such that heat is transferred through said portion of said leading edge.

14. A support rib for an aircraft wing comprising a central beam portion and a circumferentially extending portion arranged to be coupled to an inner surface of a wing leading edge, said rib comprising at least one integral heat pipe arrangement having a first end arranged in use to receive input heat and a second end arranged in use to dissipate heat.

15. A support rib as claimed in claim 14, wherein said first end of said heat pipe is arranged in said central beam portion and said second end is arranged in said circumferentially extending portion.

16. A support rib as claimed in claim 14, comprising a plurality of radially extending heat pipes arranged in use to transfer heat from said first ends to said second ends proximate a wing leading edge.

17. An aircraft wing comprising a support rib according to claim 14.

18. An aircraft heating system comprising a heat pipe and an electrically operated heating mat, said heat pipe being arranged in use to be coupled at a first end to said electrically operated heating mat and at a second end to a portion of an aircraft structure.

19. A method of heating an aircraft component by activating a heating system according to claim 18.

20. (canceled)

21. (canceled)