Turbine vane assembly with ceramic matrix composite vanes

A turbine section adapted for use in a gas turbine engine, the turbine section comprising

• a case made from metallic materials and shaped to extend around a central reference axis,
• a turbine wheel housed in the case, the turbine wheel including a disk mounted for rotation about the central reference axis relative to the case, a plurality of blades coupled to the disk for rotation with the disk, and a rotatable seal element coupled to the disk for rotation with the disk, and
• a turbine vane assembly fixed to the case and configured to smooth and redirect air moving along a primary gas path of the turbine section ahead of interaction with the turbine wheel, the turbine vane assembly including (i) a plurality of composite aero vanes made from ceramic matrix composite material shaped to provide inner and outer end walls defining the primary gas path as well as airfoils that extend across the primary gas path, (ii) a plurality of structural vanes shaped to provide airfoils that extend across the primary gas path, and (iii) a static seal element that cooperates with the rotatable seal element of the turbine wheel to provide a seal for resisting movement of gasses across the seal when the turbine section is in use within a gas turbine engine,
• wherein the airfoils of the composite aero vanes each have a first outer surface area facing the primary gas path and the airfoils of the structural vanes each have a second outer surface area facing the primary gas path that is greater than the first outer surface area, and wherein the static seal element is fixed to the plurality of structural vanes so as to be in turn coupled to the case while remaining free for relative movement in relation to the composite aero vanes so that the composite aero vanes are substantially free from carrying mechanical loads applied by pressure on the static seal element to the case.