Coating system and method for vibrational damping of gas turbine engine airfoils

A gas turbine engine blade formed of a titanium alloy and having a coating system comprising:

• a metallic coating on a surface of the blade, the metallic coating comprising metallic particles dispersed in a matrix having a metallic and/or intermetallic composition, at least some of the metallic particles having nominal dimensions of less than one micrometer, the metallic particles having compositions containing silver, the matrix consisting essentially of chromium and chromium-based intermetallic;
• and
• a ceramic coating overlying on a surface of the metallic coating;
• wherein the metallic coating is sufficiently thick to damp vibration in the blade.

A method for depositing a coating system on an airfoil of a rotating component of a turbomachine, the method comprising the steps of:

• ion plasma cleaning a surface of the airfoil;
• depositing a metallic coating on the surface of the airfoil to a sufficient thickness to damp vibration in the airfoil, the metallic coating comprising metallic particles dispersed in a matrix having a metallic and/or intermetallic composition, the metallic particles being more ductile than the matrix and having compositions containing silver and optionally tin;
• and
• depositing a ceramic coating overlying the metallic coating.