초록

A heater assembly for deicing and/or anti-icing a component includes a metallic heating element adjacent to a densely woven fabric layer impregnated with a resin that is capable of withstanding temperatures of up to 550° F. (288° C.).

대표청구항 ▼

The invention claimed is: 1. A gas turbine engine component comprising: a component body susceptible to ice formation; and an electrothermal heater assembly for anti-icing and deicing a component, the component body electrothermal heater assembly comprising: a metallic heating element; and a densel

The invention claimed is: 1. A gas turbine engine component comprising: a component body susceptible to ice formation; and an electrothermal heater assembly for anti-icing and deicing a component, the component body electrothermal heater assembly comprising: a metallic heating element; and a densely woven fabric layer adjacent to the metallic heating element and attaching the metallic heating element to the component body, the fabric layer impregnated with a thermoset adhesive capable of being load-bearing at a heater assembly operating temperature of up to 550° F., wherein the fabric layer includes a fabric material selected from a group consisting of a fiberglass fabric, a ceramic fiber fabric, polymer film, and combinations thereof; and wherein the fabric layer includes about 45 to about 70 percent by volume of the fabric material and about 30 to about 55 percent by volume thermoset adhesive. 2. The gas turbine engine component of claim 1, wherein the thermoset adhesive is selected from a group consisting of: bismaleimide, phthalonitrile, cyanate ester, polyimide adhesive, and polyimide resin. 3. The gas turbine engine component of claim 1, wherein the fabric layer is less than about 0.005 inches thick. 4. The gas turbine engine component of claim 1, wherein the metallic heating element is a titanium heating element. 5. The gas turbine engine component of claim 1, wherein the heating element has a watt density in a range of about 1 to about 50 watts/in2. 6. The gas turbine engine component of claim 1, wherein the metallic heating element is about 0.5 to about 40 mils thick. 7. The gas turbine engine component of claim 1, wherein the fabric layer exhibits a thermal conductivity value of about 10.1 BTU-in/hr-ft2-° F. 8. A gas turbine engine component comprising: a component body susceptible to ice formation; a metallic heating element, wherein the heating element has a watt density in a range of about 1 to about 50 watts/in2, and wherein the metallic heating element is about 0.5 to about 40 mils thick; and a densely woven fabric layer attached to the metallic heating element and the component body and impregnated with a thermoset adhesive capable of being load-bearing at a heater assembly operating temperature of up to 550° F., wherein the fabric layer includes a fabric material selected from a group consisting of a fiberglass fabric, a ceramic fiber fabric, polymer film, and combinations thereof; and wherein the fabric material accounts for about 45 to about 70 percent by volume of the fabric layer, wherein the fabric layer is less than about 0.005 inches thick, and wherein the fabric layer exhibits a thermal conductivity value of about 10.1 BTU-in/hr-ft2-° F. 9. The gas turbine engine component of claim 8, wherein the thermoset adhesive is selected from a group consisting of bismaleimide, phthalonitrile, cyanate ester, polyimide adhesive, and polyimide resin. 10. The gas turbine engine component of claim 8, wherein the metallic heating element is a titanium heating element. 11. The gas turbine engine component of claim 8, wherein the fabric material accounts for about 55 to about 60 percent by volume of the fabric layer. 12. A gas turbine engine component comprising: a component body susceptible to ice formation; a metallic heating element having first and second surfaces, a watt density in a range of about 1 to about 50 watts/in2, and a thickness of about 0.5 to about 40mils; and a first densely woven fabric layer adhered to the first surface of the metallic heating element and to the component body and impregnated with a thermoset adhesive capable of being load-bearing at a heater assembly operating temperature of up to 550° F., wherein the first densely woven fabric layer includes a fabric material selected from a group consisting of a fiberglass fabric, a ceramic fiber fabric, polymer film, and combinations thereof, the first densely woven fabric layer being positioned to make direct contact with a portion of the gas turbine engine component. 13. The gas turbine engine component of claim 12, wherein the first densely woven fabric layer is less than about 0.005 inches thick. 14. The gas turbine engine component of claim 12, wherein the metallic heating element is a titanium heating element. 15. The gas turbine engine component of claim 12, wherein the first densely woven fabric layer exhibits a thermal conductivity value of about 10.1 BTU-in/hr-ft2-° F. 16. The gas turbine engine component of claim 12, wherein the fabric material accounts for about 45 to about 70 percent by volume of the first densely woven fabric layer. 17. The gas turbine engine component of claim 12, and further comprising: a second densely woven fabric layer adhered to the second surface of the metallic heating element and impregnated with a resin capable of withstanding a heater assembly operating temperature of up to 550° F., wherein the second densely woven fabric layer includes of a fabric material selected from a group consisting of a fiberglass fabric, a ceramic fiber fabric, a polymer film, and combinations thereof.