Composite ice protection heater and method of producing same

• US 7,291,815 B2
• Filed: 02/24/2006
• Issued: 11/06/2007
• Est. Priority Date: 02/24/2006
• Status: Active Grant

• Current Assignee: Goodrich Corporation (Rtx Corporation), ROHR Incorporated (Rtx Corporation)
• Original Assignee: Goodrich Corporation (Rtx Corporation), ROHR Incorporated (Rtx Corporation)
• Inventors: Christy, Daniel P., Hubert, Claude M.
• Primary Examiner(s): Hoang; Tu Sa
• Assistant Examiner(s): PATEL, VINOD D
• Application Number:
  US11/276,344
• Publication Number:
  US 20070210073A1
• Time in Patent Office: 620 Days
• Field of Search: 219/535, 219/529, 219/201, 219/211, 219/520, 219/542, 244/134.D, 416/95
• US Class Current: 219/535
• CPC Class Codes: B64D 15/12 by electric heating electric heating elements in general H05B
• CPC Class Codes: B64D 2033/0206 comprising noise reduction means, e.g. acoustic liners
• CPC Class Codes: B64D 2033/0233 comprising de-icing means
• CPC Class Codes: H05B 2214/02 Heaters specially designed for de-icing or protection against icing
• CPC Class Codes: H05B 3/262 the insulating base being an insulated metal plate

Abstract

The invention includes a composite ice protection heater for an aircraft. The composite heater includes at least one electrically insulating layer, and at least one electric heater element comprising an electrically conductive layer bonded to the insulating layer. The conductive layer may include a pre-impregnated woven fabric that includes a plurality of threads that include an electrically conductive material, such as carbon or graphite fibers. The composite heater can be incorporated into a composite surface structure of an aircraft. The conductive layer and insulating layer may include a plurality of spaced openings through the layers that cooperate with an underlying open-cell matrix to attenuate noise at the associated surface of an aircraft. A desired electrical resistance of the conductive layer may be obtained by introducing a plurality of discontinuities in the layer, such as spaced holes or slits.

Claims

1. A noise-attenuating ice protection heater of an aircraft component, the heater comprising:

(a) a pair of electrically insulating layers;

(b) a plurality of spaced electric heater elements, each heater element comprising a graphite sheet disposed between the insulating layers;

(c) at least one composite support layer, wherein the electric heater elements, the insulating layers, and the support layer include a plurality of spaced openings therethrough;

(d) a pair of spaced bus strips in electrical contact with respective opposed portions of each electric heater element;

(e) an open cell matrix underlying the insulating layers, the heater elements, and the support layer;

(f) wherein the cells of the open cell matrix are in acoustic communication with the spaced openings;

(g) wherein the spaced openings are in acoustic communication with an air mass external to the heater and the aircraft component; and

(h) wherein the electrically insulating layers, the electric heater elements, the support layer, the bus strips, and the open cell matrix are bonded together to form a unitary structure.

2. An ice protection heater according to claim 1 wherein at least one electric heater element comprises a composite graphite sheet.

3. An ice protection heater according to claim 1 wherein at least one of the electrically insulating layers comprises at least one composite glass fabric layer.

4. An ice protection heater according to claim 1 wherein at least one electric heater element comprises:

(a) a woven fabric sheet comprising a plurality of warp and fill threads arranged in a weave pattern, wherein at least some of the warp threads or the fill threads are electrically conductive;

(b) wherein the weave pattern includes at least one characteristic that creates at least one locally discontinuous property in the weave pattern.

5. An ice protection heater according to claim 4 wherein the weave pattern includes at least one electrical discontinuity in at least one of the electrically conductive threads.

6. An ice protection heater according to claim 4 wherein the characteristic is an opening through the woven fabric sheet.

7. An ice protection heater according to claim 4 wherein the characteristic comprises at least one slit in the woven fabric sheet.

8. An ice protection heater according to claim 4 wherein the weave pattern includes a plurality of substantially non-conductive threads interwoven with the conductive threads.

9. An ice protection heater according to claim 4 wherein the weave pattern includes a plurality of substantially non-conductive threads interwoven with the conductive threads, and wherein the woven fabric sheet includes a first plurality of conductive threads extending in a warp direction and a second plurality of conductive threads extending in a fill direction.

10. An ice protection heater according to claim 1 wherein the spaced bus strips comprise a pair of metal strips.

11. An ice protection heater according to claim 1 wherein each of the electric heater elements is operable to be selectively energized independent of the other electric heater elements.

12. An ice protection heater according to claim 1, and further comprising at least one control device for regulating a supply of electric power to the electric heater elements.

13. An ice protection heater according to claim 1 wherein the aircraft component comprises at least a portion of an aircraft engine nacelle.