Airfoil assembly with fiber-reinforced composite rings

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, the turbine section having a plurality of airfoil assemblies disposed about a central axis of the gas turbine engine, each of the airfoil assemblies includes:
• first and second fiber-reinforced composite airfoil rings each comprised of inner and outer platform sections, a suction side wall extending between the inner and outer platforms, and a pressure side wall extending between the inner and outer platforms, the first fiber-reinforced composite airfoil ring mating at an interface with the second fiber-reinforced composite airfoil ring such that the suction side wall of the first fiber-reinforced composite airfoil ring and the pressure side wall of the second fiber-reinforced composite airfoil ring together form an airfoil that circumscribes an internal cavity, wherein the interface along the airfoil includes a gap configured to emit cooling air from the internal cavity, and a seal in the internal cavity, the seal being disposed proximate the gap, the suction side wall including a first gusset projecting into the internal cavity and the pressure side wall including a second gusset projecting into the internal cavity, the first gusset and the second gusset defining a passage there between, and the seal including an aft seal wall including inlet orifices, a forward seal wall including outlet orifices, and radially inner and outer end walls joining the forward seal wall and the aft seal wall to form a seal ring that circumscribes a seal manifold region that connects the inlet orifices and the outlet orifices to provide a flow-through passage through the seal, the forward seal wall and the aft seal wall defining a first pair of legs straddling the first gusset and a second pair of legs straddling the second gusset.