Ceramic component with support structure

A gas turbine engine, comprising:

• a compressor section;
• a combustor in fluid communication with the compressor section;
• and
• a turbine section in fluid communication with the combustor, wherein at least one of the turbine section and the compressor section includes an airfoil vane assembly, the airfoil vane assembly including:
• a vane piece having a first vane platform, a second vane platform, and a hollow airfoil section joining the first and second vane platforms;
• a spar piece having a first spar platform, a second spar platform having an extent defined between a leading edge and a trailing edge, and a spar extending between the first and second spar platforms into the hollow airfoil section;
• a seal arranged at a sealing surface of the first spar platform and sealing between the first spar platform and the first vane platform;
• and
• a thermal barrier coating disposed on the spar and substantially the extent of the spar platform of the spar piece except for the sealing surface, wherein the sealing surface is free from the thermal barrier coating.