Methods of protecting an aircraft component from ice formation

• US 8,752,279 B2
• Filed: 04/08/2011
• Issued: 06/17/2014
• Est. Priority Date: 01/04/2007
• Status: Active Grant

• Current Assignee: Goodrich Corporation (Raytheon Technologies Corporation d/b/a RTX)
• Original Assignee: Goodrich Corporation (Raytheon Technologies Corporation d/b/a RTX)
• Inventors: Brittingham, David L., Christy, Daniel P., Prybyla, Stanley G.
• Primary Examiner(s): PHAN, THIEM D
• Application Number:
  US13/082,627
• Publication Number:
  US 20110180524A1
• Time in Patent Office: 1,166 Days
• Field of Search: 296/11, 296/13, 296/19, 296/20, 219/201, 219/202, 219/529, 219/548, 219/553, 244/134.D, 244/134.E, 244/134.R, 428/293.7, 428/297.4, 428/347, 428/411.1, 428/903
• US Class Current: 29/611
• CPC Class Codes: C08J 3/18 Plasticising macromolecular compounds plasticisers C08K
• CPC Class Codes: C08L 75/04 Polyurethanes
• CPC Class Codes: H05B 2214/04 Heating means manufactured by using nanotechnology
• CPC Class Codes: Y10T 29/49083 Heater type
• CPC Class Codes: Y10T 29/49087 with envelope or housing
• CPC Class Codes: Y10T 29/49099 Coating resistive material on a base
• CPC Class Codes: Y10T 428/31504 Composite [nonstructural laminate]

Abstract

A method for protecting an aircraft component from ice formation uses a thermally conductive film. The film includes a polymer, an electrically conductive material, and a sufficient concentration of hexagonal boron nitride to provide adequate heat transfer properties, and have high thermal conductivity, peel strength, and shear strength. The films can include thermoset polymers, thermoplastic polymers, or blends thereof, and can also include reinforcing materials such as fiberglass, carbon fiber, metal mesh, and the like, and thermally conductive fillers, such as aluminum oxide, aluminum nitride, and the like. The films can be included in composite materials. The films can be used as part of a layered structure, and used in virtually any application, for example, various locations in aircraft, where heating is desirable, including nacelle skins, airplane wings, heated floor panels, and the like.

Claims

1. A method of protecting an aircraft component from ice formation, comprising:

forming a thermally conducting film from a blend of hexagonal boron nitride and a polymerizable monomer, wherein the hexagonal boron nitride is present in a concentration of from about 12 percent to about 40 percent weight, based on total weight of the film, the film also having electrically conducting material therein, the film having a thermally conductivity of at least 4 W m/k;

installing an aircraft ice protection electrothermal heater on said aircraft component, the aircraft ice protection electrothermal heater comprising;

an insulating first layer; and

the thermally conducting film over the first layer; and

supplying electrical heating energy to the aircraft ice protection electrothermal heater.

2. The method of protecting an aircraft component from ice formation according to claim 1, wherein:

the first layer is electrically insulating and thermally insulating.

3. The method of protecting an aircraft component from ice formation according to claim 1, wherein the aircraft ice protection electrothermal heater further comprises:

an electrically conducting second layer between the first layer and the film, the electrically conducting second layer comprising a heating element.

4. The method of protecting an aircraft component from ice formation according to claim 1, wherein the aircraft ice protection electrothermal heater further comprises:

an additional layer overlying the film, wherein the additional layer is capable of dissipating energy from a lightning strike.

5. The method of protecting an aircraft component from ice formation according to claim 1, wherein the aircraft ice protection electrothermal heater further comprises:

an electrically conducting second layer between the first layer and the film, the electrically conducting second layer comprising a heating element; and

an additional layer overlying the film, wherein the additional layer is capable of dissipating energy from a lightning strike; and

wherein;

the first layer is electrically insulating and thermally insulating.

6. The method of protecting an aircraft component from ice formation according to claim 1, wherein:

the electrically conducting material is selected from the group consisting of metal powders, metal-coated microspheres, metal-coated carbon-nanotubes, carbon nanofibers, carbon nanotubes, graphite nanoplatelets, copper screen, and aluminum screen.

7. The method of protecting an aircraft component from ice formation according to claim 1, wherein:

the electrically conducting material is present in a concentration sufficient to allow the film to serve as a heat source.

8. The method of protecting an aircraft component from ice formation according to claim 1, wherein:

the electrically conducting material is not present in sufficient concentration to provide the film with electrical conductivity.

9. The method of protecting an aircraft component from ice formation according to claim 1, wherein:

the hexagonal boron nitride is present in a concentration of from about 27 percent to about 33 percent weight, based on total weight of the film.

10. The method of protecting an aircraft component from ice formation according to claim 1, wherein the film further comprises:

a thermoset resin selected from the group consisting of epoxy based resin systems, matrices of bismaleimide (BMI), phenolic, polyester, PMR-15 polyimide, acetylene terminated resins, acrylics;

polyurethanes, and free-radically induced thermosetting resins.

11. The method of protecting an aircraft component from ice formation according to claim 1, wherein the film comprises an epoxy resin.

12. The method of protecting an aircraft component from ice formation according to claim 1, wherein the epoxy resin is selected from the group consisting of:

diglycidyl ethers of bisphenol A (2,2-bis(4-hydroxyphenyl)propane) or sym-tris(4-hydroxyphenyl)propane;

tris (4-hydroxyphenyl)methane;

bisphenol F;

tetrabromobisphenol A;

the polyepoxide condensation products of either bisphenol F or tetrabromobisphenol A;

cycloaliphatic epoxides;

epoxy-modified novolacs (phenoli-formaldehyde resins); and

the epoxides derived from the reaction of epichlorohydrin with analine, o-, m- or p-aminophenol, and methylene dianaline.

13. The method of protecting an aircraft component from ice formation according to claim 1, wherein the polymerizable monomer forms a thermoplastic polymer.

14. The method of protecting an aircraft component from ice formation according to claim 13, wherein:

the thermoplastic polymer is selected from polyetheretherketone (PEEK), polyetherketone (PEK), polyphenylene sulfide (PPS), polyethylene sulfide (PES), polyetherimide (PEI), polyvinylidene fluoride (PVDF), polysulfone (PS), polycarbonate (PC), polyphenylene ether/oxide, nylons, aromatic thermoplastic polyesters, aromatic polysulfones, thermoplastic polyimides, liquid crystal polymers, and thermoplastic elastomers.

15. The method of protecting an aircraft component from ice formation according to claim 13, wherein:

the hexagonal boron nitride is present in concentrations of from about 5 percent to about 50 percent by weight of the thermoplastic polymer.

16. The method according to claim 1, comprising:

supplying electrical heating energy to an electrically conducting heating element located between the insulating first layer and the film;

wherein;

the first layer is electrically insulating and thermally insulating.

17. The method according to claim 1, comprising:

supplying electrical heating energy to the film;

wherein;

the first layer is electrically insulating and thermally insulating; and

a second layer over the film is electrically insulating and thermally conducting.

18. The method according to claim 1, comprising:

forming the film from a blend of hexagonal boron nitride and a polymerizable polymer, wherein the hexagonal boron nitride has a bi-modal particle size.

19. A method of providing an aircraft with an ice protection system, comprising:

forming a thermally conducting film from a blend of hexagonal boron nitride and a polymerizable monomer, wherein the hexagonal boron nitride is present in a concentration of from about 12 percent to about 40 percent weight, based on total weight of the film, the film also having electrically conducting material therein, the film having a thermally conductivity of at least 4 W m/k; and

providing a surface of the aircraft with an aircraft ice protection electrothermal heater comprising;

an insulating first layer; and

the thermally conducting film over the first layer.

20. The method according to claim 19, comprising:

forming the film from a blend of hexagonal boron nitride and a polymerizable polymer, wherein the hexagonal boron nitride has a bi-modal particle size.