Abstract: A gas turbine engine component having a coating with a temperature dependent transparency is disclosed. The component includes a substrate having an optically absorptive surface and a coating disposed over the substrate that has a reflectivity that is temperature dependent. At temperatures below the glass transition temperature, the coating has a low transparency to incident radiation and is highly reflective, while at higher temperatures, the coating has a high transparency to incident radiation. As a result of the increased transparency at high temperatures, incident radiation passes through the coating and is absorbed by the optically absorptive surface of the substrate underlying the coating. At low temperatures, when the coating has a high reflectivity, incident radiation is reflected by the component.

Abstract: A gas turbine engine component having a coating with a temperature dependent transparency is disclosed. The component includes a substrate having an optically reflective surface and a coating disposed over the substrate that has a transparency that is temperature dependent. At temperatures below the glass transition temperature, the coating has a low transparency to incident radiation, while at higher temperatures, the coating has a high transparency to incident radiation. As a result of the increased transparency at high temperatures, incident radiation passes through the coating and is reflected off of the optically reflective surface of the substrate underlying the coating. At low temperatures, when the coating has a low transparency, incident radiation is absorbed by the component, resulting in lower reflectivity.