Enhanced adhesion thermal barrier coating

A gas turbine engine comprising:

• a compressor section;
• a combustor section fluidly connected to the compressor section;
• a turbine section fluidly connected to the combustor section;
• a plurality of gas path components exposed to a primary fluid flowpath through said compressor section, said combustor section and said turbine section, at least one of said gas path components including
• an exterior facing surface;
• a lattice structure extending outward from the exterior facing surface, the lattice structure being integral to the exterior facing surface and comprising partial additive manufacturing supports, wherein the exterior facing surface and the lattice structure have a combined surface roughness (Ra) in the range of 100-600, wherein the partial additive manufacturing supports are attached to, and integral to, the exterior facing surface and are remnant structures remaining after removal of an additive manufacturing support;
• and
• a thermal barrier coating adhered to at least a portion of the exterior facing surface and the lattice structure.