| 摘要 |
<p>A coating (403) and a method for forming the coating (403), the method including coating a surface of a gas turbine engine turbine component having a metallic surface that is outside the combustion gas stream and exposed to cooling air during operation of the engine. A gel-forming solution including a ceramic metal oxide precursor is provided. The gel-forming solution is heated to a first preselected temperature for a first preselected time to form a gel. The gel is then deposited on the metallic surface. Thereafter the gel is fired at a second preselected temperature above the first preselected temperature to form a ceramic corrosion resistant coating (403) comprising a ceramic metal oxide is selected from the group consisting of zirconia, hafnia and combinations thereof. The ceramic corrosion resistant coating (403) having a thickness of up to about 127 microns and remaining adherent at temperatures greater than about 1000 °F.</p> |
