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A high temperature gas turbine component for use in the gas flow path that also is a specular optical reflector. A thin layer of a high temperature reflector is applied to the gas flow path of the component, that is, the surface of the component that forms a boundary for hot combustion gases. The co

A high temperature gas turbine component for use in the gas flow path that also is a specular optical reflector. A thin layer of a high temperature reflector is applied to the gas flow path of the component, that is, the surface of the component that forms a boundary for hot combustion gases. The component typically includes a thermal barrier coating overlying the high temperature metallic component that permits the component to operate at elevated temperatures. The thermal barrier coating must be polished in order to provide a surface that can suitably reflect the radiation into the gas flow path. A thin layer of the high temperature reflector the is applied over the polished thermal barrier coating by a process that can adequately adhere the reflector to the polished surface without increasing the roughness of the surface. The high temperature reflector can be applied to any surface aft of the compressor, such as on a turbine nozzle. The surface reflects radiation back into the hot gas flow path. The reflected radiation is not focused onto any other hardware component. The design of the component is such that the radiation is returned to the gas flow path rather than absorbed into a component wall that only serves to increase the temperature of the wall.

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1. A component having a specular reflective surface for use in a hot flow path of a high temperature device in which hot gaseous fluids traverse the device in a hot flow path, the component comprising:a substrate material having a surface that forms a boundary for hot gaseous fluids of combustion; a

1. A component having a specular reflective surface for use in a hot flow path of a high temperature device in which hot gaseous fluids traverse the device in a hot flow path, the component comprising:a substrate material having a surface that forms a boundary for hot gaseous fluids of combustion; and a single layer of specular reflective coating having a predetermined thickness overlying the substrate surface forming the hot fluid boundary, the specular reflective material having an applied roughness sufficiently smooth, and having a high temperature capability to survive temperatures in the hot flow path so that a surface of the specular reflective material reflects a least about 80% of incident radiation away from its surface to the fluids in the hot flow path and wherein the coating is not subject to oxidation due to contact with the hot gaseous fluids. 2. The component of claim 1 wherein the device is a gas turbine engine.3. The component of claim 1 wherein the component is an afterburner liner.4. The component of claim 1 wherein the component is a flameholder.5. The component of claim 1 further including a ceramic material between the substrate material and the specular reflective coating, the ceramic material forming a thermal barrier overlying the substrate material, a surface of the ceramic material opposite the substrate and adjacent the specular reflective coating having a surface roughness about 50 micro inches and smoother.6. A turbine nozzle component having a specular reflective surface for use in a hot flow path of a high temperature device in which hot gaseous fluids traverse the device in a hot flow path, the component comprising:a substrate material wherein the specular reflective surface form a boundary for hot gaseous fluids of combustion; and a single layer of specular reflective coating having a predetermined thickness overlying the substrate surface forming the hot fluid boundary, the specular reflective material having an applied roughness sufficiently smooth, and having a high temperature capability so that a surface of the specular reflective material reflects a least about 80% of incident radiation away from its surface to the gases in the hot flow path and wherein the coating is not subject to oxidation due to contact with the hot gaseous fluids. 7. The turbine nozzle component of claim 6 wherein the component is a turbine vane.8. The turbine nozzle component of claim 6 further including a ceramic material between the substrate material and the specular reflective coating, the ceramic material forming a thermal barrier overlying the substrate material, a surface of the ceramic material opposite the substrate and adjacent the specular reflective coating having a surface roughness about 100 micro inches and smoother and the surface of the specular reflective coating having a surface finish of 100 micro inches and smoother.9. The turbine nozzle component of claim 8 wherein the turbine nozzle component is a turbine nozzle vane wherein the substrate material has a leading edge and a trailing edge and wherein the specular reflective coating is only applied to the leading edge.10. The turbine nozzle component of claim 9 wherein the surface of the ceramic material opposite the substrate and adjacent the specular reflective coating has a surface roughness about 50 micro inches and smoother.11. The turbine nozzle component of claim 9 wherein the surface of the ceramic material opposite the substrate and adjacent the specular reflective coating has a surface roughness about 32 micro inches and smoother.12. The turbine nozzle component of claim 9 wherein the specular reflective coating is selected from the group of materials consisting of platinum, palladium, a dielectric mirror comprising tantalum oxide (TaO2), a dielectiic mirror comprising silica (SiO2), a dielectric mirror comprising titanium dioxide (TiO2) and combinations thereof.13. The turbine nozzle component of claim 9 wherein the coating is applied to a predetermined thickness up to about 10 microns.14. The turbine component of claim 9 wherein the coating is applied to a predetermined thickness about 1 micron and less, and forms a continuous coating.15. The component of claim 14 further characterized by a temperature performance improvement of about 100° F. over a component without the specular coating.16. The component of claim 6 wherein the substrate material is a high temperature superalloy selected from the group consisting of a superalloy selected from the group consisting of Fe, Co, Ni and combinations thereof.17. A method for manufacturing a turbine nozzle having a specular reflective surface for use in a hot flow path of a gas turbine engine, the method comprising the steps of:providing a turbine nozzle vane having a leading edge and a trailing edge comprised of a substrate material; applying a ceramic thermal barrier coating system over the substrate surface of at least the leading edge of the turbine nozzle vane forming the hot fluid boundary; mechanically working a surface of a ceramic coating forming the outer layer of the thermal barrier coating system, overlying and opposite the substrate surface to obtain a surface finish of about 100 micro inches and smoother; applying a specular reflective coating over the surface of the ceramic coating to a predetermined thickness, the method for applying the coating providing a coating surface finish of about 100 micro inches and smoother, an outer surface of the specular reflective coating opposite the ceramic coating being exposed to gaseous fluids in the hot flow path of the engine. 18. The method of claim 17 wherein the step of mechanically working the surface of the ceramic coating further includes obtaining a surface finish of about 50 micro inches and smoother.19. The method of claim 17 wherein the step of mechanically working the surface of the ceramic coating further includes obtaining a surface finish of about 32 micro inches and smoother.20. The method of claim 17 wherein the step of applying the specular reflective coating over the surface of the ceramic coating to a predetermined thickness includes applying the coating to a thickness of up to about 10 microns.21. A component having a specular reflective surface for use in a hot flow path of a high temperature device in which hot gaseous fluids traverse the device in a hot flow path, the component comprising:a substrate material having a surface that forms a boundary for hot gaseous fluids of combustion; a specular reflective coating having a predetermined thickness overlying the substrate surface forming the hot fluid boundary, the specular reflective material having an applied roughness sufficiently smooth, and having a high temperature capability to survive temperatures in the hot flow path so that a surface of the specular reflective material reflects at least about 80% of incident radiation away from its surface to the fluids in the hot flow path and wherein the coating is not subject to oxidation due to contact with the hot gaseous fluids; and a ceramic material between the substrate material and the specular reflective coating, the ceramic material forming a thermal barrier overlying the substrate material, a surface of the ceramic material opposite the substrate and adjacent the specular reflective coating having a surface roughness about 50 micro inches and smoother. 22. A turbine nozzle component having a specular reflective surface for use in a hot flow path of a high temperature device in which hot gaseous fluids traverse the device in a hot flow path, the component comprising:a substrate material wherein the specular reflective surface forms a boundary for hot gaseous fluids of combustion; a specular reflective coating having a predetermined thickness overlying the substrate surface forming the hot fluid boundary, the specular reflective material having an applied roughness sufficiently smooth, and having a high temperature capability so that a surface of the specular reflective material reflects at least about 80% of incident radiation away from its surface to the gases in the hot flow path and wherein the coating is not subject to oxidation due to contact with the hot gaseous fluids; and a ceramic material between the substrate material and the specular reflective coating, the ceramic material forming a thermal barrier overlying the substrate material, a surface of the ceramic material opposite the substrate and adjacent the specular reflective coating having a surface roughness about 100 micro inches and smoother and the surface of the specular reflective coating having a surface finish of 100 micro inches and smoother. 23. The turbine nozzle component of claim 22 wherein the turbine nozzle component is a turbine nozzle vane wherein the substrate material has a leading edge and a trailing edge and wherein the specular reflective coating is only applied to the leading edge.24. The turbine nozzle component of claim 22 wherein the surface of the ceramic material apposite the substrate and adjacent the specular reflective coating has a surface roughness about 50 micro inches and smoother.25. The turbine nozzle component of claim 22 wherein the surface of the ceramic material opposite the substrate and adjacent the specular reflective coating has a surface roughness about 32 micro inches and smoother.26. The turbine nozzle component of claim 22 wherein the specular reflective coating is selected from the group of materials consisting of platinum, palladium, a dielectric mirror comprising tantalum oxide (TaO2), a dielectric mirror comprising silica (SiO2), a dielectric mirror comprising titanium dioxide (TiO2) and combinations thereof.27. The turbine nozzle component of claim 22 wherein the coating is applied to a predetermined thickness up to about 10 microns.28. The turbine component of claim 22 wherein the coating is applied to a predetermined thickness about 1 micron and less, and forms a continuous coating.29. The component of claim 28 further characterized by a temperature performance improvement of about 100 ° F. over a component without the specular coating.