Method of applying a metallic heat rejection coating onto a gas turbine engine component

A method of applying a heat-rejection coating, comprising the steps of:

• supplying a metallic component of a gas turbine engine;
• applying a ceramic barrier coating onto the component, wherein the step of applying the ceramic barrier coating includes the steps of
• air-assisted spraying the ceramic-barrier-coating mixture onto the component, and
• drying the ceramic-barrier-coating mixture;
• applying a reflective-coating mixture onto the ceramic barrier coating applied to the component, wherein the reflective-coating mixture comprises a metallic pigment and a reflective-coating-mixture carrier, and wherein the step of applying is accomplished by a method selected from the group consisting of air-assisted spraying, airless spraying, brushing, and decal transfer;
• and
• firing the component having the reflective-coating mixture thereon to form a reflective coating on the component.

A method of applying a heat-rejection coating, comprising the steps of:

• supplying a metallic component of a gas turbine engine, the component being made of a nickel-base superalloy and having a component surface;
• pre-treating the component surface of the component to form a pre-treated component surface, wherein the step of pre-treating the component surface includes the step of
• polishing the component surface, thereafter
• pre-oxidizing the component surface, and thereafter
• applying a ceramic barrier coating onto the component surface, wherein the step of applying the ceramic barrier coating includes the steps of
• air-assisted spraying a ceramic-barrier-coating mixture onto the component, and
• drying the ceramic-barrier-coating mixture;
• thereafter
• air-assisted spraying a reflective-coating mixture onto the pre-treated component surface, the reflective-coating mixture comprising a metallic pigment and a reflective-coating-mixture carrier;
• and
• firing the component having the coating mixture thereon.

A method of applying a heat-rejection coating, comprising the steps of:

• supplying a metallic component of a gas turbine engine, the component being made of a nickel-base superalloy and having a component surface;
• pre-treating the component surface of the component to form a pre-treated component surface, and step of pre-treating including the steps of
• polishing the component surface, thereafter
• pre-oxidizing the component surface, thereafter
• air-assisted spraying a ceramic-barrier-coating mixture onto the component surface, and thereafter
• drying the ceramic-barrier-coating mixture to form a ceramic barrier coating on the component, the ceramic barrier coating being present in an amount of from about 0.0005 to about 0.0015 grams per square inch of the pre-treated component surface;
• thereafter
• air-assisted spraying a reflective-coating mixture onto the pre-treated component surface, the reflective-coating mixture comprising
• a metallic pigment selected from the group consisting of platinum, gold, palladium, and alloys thereof, and
• an organic reflective-coating-mixture carrier;
• and
• firing the component having the reflective-coating mixture thereon to form a reflective coating, the reflective coating and the ceramic barrier coating being together present in an amount of from about 0.00325 to about 0.00625 grams per square inch of the component surface.