Turbine blade outermost abrasive layer using graded ceramics

A turbine blade, comprising:

• an airfoil body having a radial outermost surface relative to a turbine rotor;
• a bond coat over the radial outermost surface;
• and
• an outermost abrasive layer over the bond coat, wherein the outermost abrasive layer includes a graded metal ceramic layer including:
• a first layer over the bond coat consisting of a first ceramic consisting of 8 weight % yttria stabilized zirconia (8YSZ) having a porosity between 5-25%;
• a second layer over the first layer including 65-85 weight % of a metal and 15-35 weight % of a second ceramic;
• a third layer over the second layer including 40-60 weight % of the metal and 40-60 weight % of the second ceramic;
• a fourth layer over the third layer including 5-25 weight % of the metal and 75-95 weight % of the second ceramic;
• and
• a fifth layer over the fourth layer including 0 weight % of the metal and 100 weight % of the second ceramic.

A method of forming an outermost abrasive layer for a radial outermost surface of a turbine blade, the method comprising:

• forming a bond coat on the radial outermost surface of the turbine blade;
• forming one of a graded oxide ceramic layer and a graded metal ceramic layer over the bond coat on the radial outermost surface of the turbine blade;
• and
• heat treating the one of the graded oxide ceramic layer and the graded metal ceramic layer on the radial outermost surface of the turbine blade.