초록 ▼

A high emissivity (Hi-E) coating for use on the exhaust baffles of HIRSS systems. HIRSS systems were developed to reduce the infrared (IR) signature of helicopter engines. Increasing operating temperatures of helicopter engines have made the HIRSS systems less effective. An infrared coating applied

A high emissivity (Hi-E) coating for use on the exhaust baffles of HIRSS systems. HIRSS systems were developed to reduce the infrared (IR) signature of helicopter engines. Increasing operating temperatures of helicopter engines have made the HIRSS systems less effective. An infrared coating applied over selected portions of the HIRSS reduces the IR of the system. The Hi-E coating comprises, in weight percent, 30-80% refractory oxide pigment, 5-20% binder, 1-15% potassium oxide, optionally up to about 15% glass-forming material and the balance refractory oxide powder. When applied to provide a surface finish of 1100Ra microinches or coarser, the coated HIRSS has a significantly reduced hemispherical reflectance in the IR frequency range.

대표청구항 ▼

What is claimed is: 1. A hover infrared suppression system for a gas turbine engine comprising: a hover infrared suppression system having an upstream first stage, a second stage downstream from the first stage and a third stage downstream from the second stage, the engine operating as a temperatur

What is claimed is: 1. A hover infrared suppression system for a gas turbine engine comprising: a hover infrared suppression system having an upstream first stage, a second stage downstream from the first stage and a third stage downstream from the second stage, the engine operating as a temperature sufficient to cause the hover infrared suppression system to emit infrared radiation; a high emissivity coating applied over at least one of the stages of the hover infrared suppression system to reduce the infrared radiation emitted from the engine; and wherein the high emissivity coating as applied, comprises, in weight percent, about 30-80% refractory oxide pigment, about 5-20% binder, about 1-15% potassium oxide, optionally up to about 15% glass-forming material and the balance refractory oxide powder. 2. The infrared suppression system of claim 1 wherein the high emissivity coating is applied to the second stage of the hover infrared suppression system, wherein the second stage is intermediate between the upstream first stage and the downstream third stage, the second stage including an upstream end and a downstream end, the downstream end of the second stage including a flange overlapping an upstream end of the third stage. 3. The infrared suppression system of claim 2 wherein the high emissivity coating is applied to a surface of the second stage flange. 4. The infrared suppression system of claim 3 wherein the high emissivity coating is applied to an inner diameter of the second stage flange. 5. The infrared suppression system of claim 3 wherein the high emissivity coating is applied to an inside surface of the second stage flange. 6. The infrared suppression system of claim 1 wherein the high emissivity coating is applied to the second stage. 7. The infrared suppression system of claim 6 wherein the high emissivity coating is applied to an aft rear face of the baffle system. 8. The infrared suppression system of claim 6 wherein the high emissivity coating is applied to a D-ring concave surface. 9. The infrared suppression system of claim 6 wherein the high emissivity coating is applied to a D-ring strut. 10. The infrared suppression system of claim 6 wherein the high emissivity coating is applied to baffle system D-rings. 11. The infrared suppression system of claim 6 wherein the high emissivity coating is applied to baffle system flaps. 12. A high emissivity coating for application to a hover infrared suppression system having three stages, the coating applied to at least one of the stages to reduce the infrared radiation emitted from the engine, comprising as applied, in weight percent, about 30-80% refractory oxide pigment, about 5-20% binder, about 1-15% potassium oxide, optionally up to about 15% glass-forming material and the balance refractory oxide powder. 13. The high emissivity coating of claim 12 wherein the refractory oxide pigment includes about 30-80% lanthanum strontium manganate. 14. The high emissivity coating of claim 12 wherein the binder is a material that forms a matrix. 15. The high emissivity coating of claim 12 wherein the binder forms a silicate matrix. 16. The high emissivity coating of claim 15 wherein the binder is selected from the group consisting of potassium silicate, sodium silicate, lithium silicate and aluminum silicate. 17. The high emissivity coating of claim 12 wherein the optional glass-forming material promotes the formation of a glassy matrix. 18. The high emissivity coating of claim 17 wherein the optional glass forming material is TiO2. 19. The high emissivity coating of claim 12 wherein the refractory oxide material is selected from the group consisting of Al2O3, magnesium oxide, zirconium oxide, hafnium oxide and chromium oxide. 20. A method for applying a high emissivity coating to a hover infrared suppression system comprising the steps of: providing a hover infrared suppression system: preselecting surfaces of the suppression system for coating; providing a high emissivity coating comprising, in weight percent, about 30-80% refractory oxide pigment, about 5-20% binder, about 1-15% potassium oxide, optionally up to about 15% glass-forming material and the balance refractory oxide powder; grit blasting the preselected surfaces to provide a grit blasted surface finish; applying a coating of NiCrAlY by wire spraying over the grit blasted surface finish to provide a surface finish of about 1100 microinches Ra; adding water to the coating to provide a predetermined viscosity and mixing; applying the high emissivity coating to a preselected thickness over the NiCrAlY coating; drying the high emissivity coating evaporating the water; repeating the steps of applying the coating and allowing the coating to dry until a thickness of about 0.001-0.012 inches is achieved and a coating surface finish of at least about 1100 microinches Ra is achieved; heating the applied, dried coating at a rate of about 10�� F./min. to a firing temperature of at least about 1200�� F. to obtaing a surface finish of 1100 microinches Ra or rougher, the coating reducing the hemispherical reflectance of infrared radiation of the hover infrared suppression system as compared to uncoated hover infrared suppression systems by at least about 15-20% at angles perpendicular to the surface.