| 摘要 |
Methods are provided for forming a coating system on a gas turbine component. In one embodiment, and by way of example only, the method includes cold spraying a material onto the component surface to form an overlay coating, the material comprising MCrAlY, wherein M comprises a constituent selected from the group consisting of Ni, Co, or Fe, or combinations of Ni, Co, and Fe. Then, the overlay coating is heat treated. The overlay coating is then shot peened and vibro polished. A thermal barrier coating is then applied onto the overlay coating to form the coating system via air plasma spaying or electron beam physical vapor deposition technique.
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