Pulsed electrothermal ice protection systems with coated heating substrates

Patent metadata

Field	Value
Publication number	US-10358224-B2
Application number	US-201313874910-A
Country	US
Kind code	B2
Filing date	May 1, 2013
Priority date	May 1, 2013
Publication date	Jul 23, 2019
Grant date	Jul 23, 2019

Abstract

An aircraft ice protection system includes a heating substrate with a coating in intimate thermal contact with the heating substrate. The thermal effusivities of the heating substrate and the coating are different from one another for interference of thermal waves reflected from the coating with thermal waves generated in the heating substrate. A pulse generator can be operatively connected to the heating substrate to convert pulsed electrical power from the pulse generator into thermal energy for ice removal or prevention.

First claim

What is claimed is:

1. An aircraft ice protection system comprising:
a heating substrate; and
a coating in intimate physical and thermal contact with the heating substrate, wherein the thermal effusivity of the coating is greater than that of the heating substrate for interference of thermal waves reflected from the coating with thermal waves generated in the heating substrate, wherein the coating is on the order of a fraction of a micron thick.

2. An aircraft ice protection system as recited in claim 1 , further comprising a pulse generator operatively connected to the heating substrate to convert pulsed electrical power from the pulse generator into thermal energy for ice removal or prevention of ice formation.

3. An aircraft ice protection system as recited in claim 2 , wherein the thermal effusivity of the coating is greater than the thermal effusivity of the heating substrate for constructive interference of thermal waves reflected from the coating with thermal waves generated in the heating substrate to boost the peak temperature of the heating substrate and coating under pulsed electrical power from the pulse generator.

4. An aircraft ice protection system as recited in claim 2 , wherein the heating substrate is operatively connected to the pulse generator as a resistive heater.

5. An aircraft ice protection system as recited in claim 2 , wherein the pulse generator includes a capacitor bank operatively connected to apply an electrical pulse to the heating substrate.

6. An aircraft ice protection system as recited in claim 1 , wherein the heating substrate is metallic or composite.

7. An aircraft ice protection system as recited in claim 1 , wherein the coating is a metallic film.

8. An aircraft ice protection system as recited in claim 1 , wherein the coating is disposed on an ice side of the heating substrate where ice is melted when the system is in use.

9. An aircraft ice protection system as recited in claim 1 , wherein the coating is disposed on a side of the heating substrate opposite to where ice is melted when the system is in use.

10. An aircraft ice protection system as recited in claim 1 , wherein the coating has a thickness thinner than that of the heating substrate.

11. An aircraft ice protection system as recited in claim 1 , wherein the coating has a thickness on the order of about the thermal diffusion length of the thermal wave.

12. A method of ice protecting a surface comprising:
applying an electrical pulse to a heating substrate to generate a thermal wave; and
reflecting a portion of the thermal wave into the heating substrate from a coating on a surface of the substrate to interfere the reflected portion with the thermal wave, wherein the thermal effusivity of the coating is greater than that of the heating substrate, and wherein the coating is on the order of a fraction of a micron thick.

13. A method as recited in claim 12 , wherein reflecting a portion of the thermal wave includes constructively interfering the reflected portion of the thermal wave with the thermal wave to boost the temperature of the substrate for ice removal.

14. A method as recited in claim 12 , wherein applying an electrical pulse includes heating the heating substrate through resistive heating during a pulse from an electrical pulse generator.

15. A method as recited in claim 12 , wherein reflecting a portion of the thermal wave includes reflecting a thermal wave wherein the substrate is metallic or a conductive composite material, and wherein the coating is a metallic film with an effusivity greater than that of the heating substrate.

16. A method as recited in claim 12 , further comprising melting ice from a side of the heating substrate having the coating thereon.

17. A method as recited in claim 12 , further comprising melting ice from a side of the heating substrate opposite the coating.

18. A method as recited in claim 12 , wherein applying an electrical pulse includes discharging stored energy in a capacitor bank electrically coupled to the heating substrate.

19. A method as recited in claim 18 , wherein the step of discharging the stored energy in a capacitor bank is repeated periodically for an extended ice removal interval.

Assignees

• Goodrich Corp

Inventors

• Hamm Richard Roy

Classifications

• B64D15/14

  controlled cyclically along length of surface · CPC title

• B64D15/12 Primary

  by electric heating (heating arrangements specially adapted for transparent or reflecting areas H05B3/84) · CPC title