Electrothermal de-icing system

• US 5,657,951 A
• Filed: 06/23/1995
• Issued: 08/19/1997
• Est. Priority Date: 06/23/1995
• Status: Expired due to Term

• Current Assignee: Goodrich Corporation (Raytheon Technologies Corporation d/b/a RTX)
• Original Assignee: Goodrich Corporation (Raytheon Technologies Corporation d/b/a RTX)
• Inventors: Giamati, Michael J.
• Primary Examiner(s): Kashnikow, Andres
• Assistant Examiner(s): MARQUIS, LISSI MOJICA
• Application Number:
  US08/494,268
• Time in Patent Office: 788 Days
• Field of Search: 244/134 R, 244/134 D, 244/134 E, 219/121.65, 219/121.66, 219/202
• US Class Current: 244/134.00D
• CPC Class Codes: B64D 15/14 controlled cyclically along length of surface

Abstract

A de-icing system is provided including a de-icer attached to an aircraft structural member subjected to an impinging airstream during flight, the airstream passing over the structural member in a fore to aft direction. The deicer has a primary heater element disposed beneath a primary shedding zone upon which ice accumulates during flight, the primary heater element being configured to heat the primary shedding zone upon application of an electrical potential across the primary heater element, and a secondary heater element disposed beneath a secondary shedding zone upon which ice accumulates during flight, the secondary heater element being configured to heat the secondary shedding zone upon application of an electrical potential across the secondary heater element, the secondary heater element being disposed immediately aft of the primary heater element. The de-icing system also has a controller configured to heat the primary heating element for a period of time sufficient to induce ice to shed from the primary shedding zone, to subsequently allow the primary heating element to cool below freezing, and to subsequently heat the secondary heating element for a period of time sufficient to induce ice to shed from the secondary shedding zone. The invention reduces runback and refreeze in unheated areas.

Claims

1. A de-icing system including a de-icer attached to an aircraft structural member subjected to an impinging airstream during flight, said airstream passing over said structural member in a fore to aft direction, comprising:

a primary heater element disposed beneath a primary shedding zone upon which ice accumulates during flight said primary heater element being configured to heat said primary shedding zone upon application of an electrical potential across said primary heater element;

a secondary heater element disposed beneath a secondary shedding zone upon which ice accumulates during flight, said secondary heater element being configured to heat said secondary shedding zone upon application of an electrical potential across said secondary heater element, said secondary heater element being disposed immediately aft of said primary heater element; and

,

a controller configured to energize said primary heating element for a period of time sufficient to induce ice to shed from said primary shedding zone, to subsequently de-energize said primary heating element and allow said primary shedding zone to cool below freezing, and to subsequently energize said secondary heating element for a period of time sufficient to induce ice to shed from said secondary shedding zone while said primary shedding zone is below freezing.

2. The de-icing system of claim 1, further comprising a parting strip heater element disposed immediately fore of said primary heater element beneath a parting strip zone, said parting strip element being configured to heat said parting strip zone upon application of an electrical potential across said parting strip element;

and,

wherein said controller is configured to heat said parting strip heater element to maintain said parting strip zone above freezing during flight in icing conditions.

3. The de-icing system of claim 2, wherein said controller is configured to decrease an average electrical power consumed by said parting strip heater as outside air temperature increases.

4. The de-icing system of claim 2, further comprising a temperature sensor adjacent said parting strip heater element, and said controller is configured to heat said parting strip heater element if a temperature sensed by said temperature sensor is less than a lower setpoint, and to stop heating said parting strip heater element if said temperature sensed by said temperature sensor is greater than an upper setpoint, said controller being configured to decrease said lower and upper setpoints as outside air temperature decreases.

5. The de-icing system of claim 1, wherein said controller is configured to subsequently heat said secondary shedding zone after said primary shedding zone cools to slightly below freezing.

6. The de-icing system of claim 1, comprising a plurality of primary heater elements and a plurality of secondary heater elements, each primary heater element having a secondary zone disposed immediately aft of that primary heating element.

7. The de-icing system of claim 1, comprising a plurality of primary heater elements and a plurality of secondary heater elements, each primary heater element having a secondary zone disposed immediately aft of that primary heating element;

and,

wherein said structural member is an airfoil having a convex leading edge, at least one of said primary elements being disposed on either side of said leading edge.

8. The de-icing system of claim 7, further comprising a parting strip heater element disposed between said primary heater element disposed on either side of said convex leading edge beneath a parting strip zone, said parting strip element being configured to heat said parting strip zone upon application of an electrical potential across said parting strip element;

and,

wherein said controller is configured to heat said parting strip heater element and maintain said parting strip zone above freezing during flight in icing conditions.

9. The de-icer of claim 1, wherein said controller is configured to heat said secondary heater element for a period of time sufficient for heat to flow into said primary zone thereby inducing ice to shed from said primary shedding zone without heating said primary heater element during at least one cycle.

10. The de-icer of claim 2, wherein said controller is configured to heat said secondary heater element for a period of time sufficient for heat to flow into said primary zone thereby inducing ice to shed from said primary shedding zone without heating said primary heater element during at least one cycle.

11. A method for de-icing an aircraft structural member subjected to an impinging airstream during flight, said airstream passing over said structural member in a fore to aft direction, comprising the steps of:

energizing a primary heating element disposed beneath a primary shedding zone upon which ice accumulates during flight, said primary heating element being energized for a period of time sufficient to induce ice to shed from said primary shedding zone by applying an electrical potential across said primary heater element;

subsequently de-energizing said primary heating element and allowing said primary shedding zone to cool below freezing; and

,

subsequently energizing a secondary heating element disposed beneath a secondary shedding zone upon which ice accumulates during flight, said secondary heating element being energized for a period of time sufficient to induce ice to shed from said secondary shedding zone by applying an electrical potential across said secondary heating element while said primary shedding zone is below freezing, said secondary heating element being disposed immediately aft of said primary heater element.

12. The method of claim 11, further comprising a parting strip heater element disposed immediately fore of said primary heater element beneath a parting strip zone, said parting strip element being configured to heat said parting strip zone upon application of an electrical potential across said parting strip element;

and,

further comprising the step of heating said parting strip heater element to maintain said parting strip zone above freezing during flight in icing conditions.

13. The method of claim 12, further comprising the step of decreasing an average electrical power consumed by said parting strip heater as outside air temperature increases.

14. The method of claim 12, further comprising a temperature sensor adjacent said parting strip heater element, and further comprising the steps of heating said parting strip heater element if a temperature sensed by said temperature sensor is less than a lower setpoint, and stopping heating of said parting strip heater element if said temperature sensed by said temperature sensor is greater than an upper setpoint, and decreasing said lower and upper setpoints as outside air temperature decreases.

15. The method of claim 11, wherein said secondary shedding zone is heated after said primary shedding zone cools to slightly below freezing.

16. The method of claim 11, comprising the steps of heating a plurality of primary heater elements and heating a plurality of secondary heater elements, each primary heater element having a secondary zone disposed immediately aft of that primary heating element.

17. The method of claim 11, comprising the steps of heating a plurality of primary heater elements and heating a plurality of secondary heater elements, each primary heater element having a secondary zone disposed immediately aft of that primary heating element;

and,

wherein said structural member is an airfoil having a convex leading edge, at least one of said primary elements being disposed on either side of said leading edge.

18. The method of claim 17, further comprising a parting strip heater element disposed between said primary heater element disposed on either side of said convex leading edge beneath a parting strip zone, said parting strip element being configured to heat said parting strip zone upon application of an electrical potential across said parting strip element;

and,

further comprising the step of heating said parting strip heater element to maintain said parting strip zone above freezing during flight in icing conditions.

19. The de-icer of claim 11, further comprising the step of heating said secondary heater element for a period of time sufficient for heat to flow into said primary zone thereby inducing ice to shed from said primary shedding zone without heating said primary heater element during at least one cycle.

20. The de-icer of claim 12, further comprising the step of heating said secondary heater element for a period of time sufficient for heat to flow into said primary zone thereby inducing ice to shed from said primary shedding zone without heating said primary heater element during at least one cycle.