Turbomachine airfoil having a variable thickness thermal barrier coating

A turbomachine comprising;

• a compressor;
• a combustor disposed downstream from the compressor;
• and
• a turbine disposed downstream from the combustor, the turbine comprising a rotor blade and a stator vane, at least one of the rotor blade and the stator vane comprising an airfoil, the airfoil comprising:
• a root;
• a tip spaced radially from the root, the root and the tip defining a span of the airfoil therebetween;
• a leading edge extending across the span of the airfoil from the root to the tip;
• a trailing edge downstream of the leading edge along a flow direction, the trailing edge extending across the span of the airfoil from the root to the tip;
• a pressure side surface extending between the root and the tip and extending between the leading edge and the trailing edge;
• a suction side surface extending between the root and the tip and extending between the leading edge and the trailing edge, the suction side surface opposing the pressure side surface;
• and
• a thermal barrier coating on the pressure side surface and the suction side surface, the thermal barrier coating comprising a base layer and a top coat on top of at least a portion of the base layer, wherein a thickness of the base layer decreases by constant transitions in the thickness from the leading edge to the trailing edge across each of the pressure side surface and the suction side surface with a maximum thickness of the base layer at the leading edge, and wherein a thickness of the top coat increases from the leading edge towards the trailing edge across each of the pressure side surface and the suction side surface.