Patent ID: 8420180

Claim:
A method of coating a gas turbine engine component using a powder coating process to produce a tightly adherent coating comprising: providing a gas turbine engine component having a solid surface; applying a powder coating to the gas turbine engine component solid surface using the powder coating process, wherein the powder coating is applied in a dry form without an organic solvent, the powder coating comprising fritted glass particles and ceramic particles; heating the applied powder coating to a temperature sufficient to raise the melting point of the powder coating to melt particles of the powder coating to form a glass matrix with ceramic particles trapped in the matrix; wherein heating to the temperature sufficient to melt particles of the powder further fuses the molten powder to the gas turbine engine component solid surface and cures the powder coating on the surface; wherein the coating and heating are performed in less than 15 minutes; and wherein the cured coating is tightly adherent to the component.