CMC component flow discourager flanges

A turbine for a gas turbine engine, comprising:

• a plurality of vanes arranged circumferentially about an engine axis, each vane comprising:
• a support structure that is a unitary component having an axial portion extending in an axial direction and a radial portion extending in an axial direction, the axial and radial directions relative to the engine axis;
• an outer portion arranged between the support structure and a flow path, the outer portion formed from a ceramic material, the outer portion including an internal cavity that receives the radial portion of the support structure and that is dimensioned to receive cooling flow from the axial portion of the support structure, the outer portion and the axial portion of the support structure opposed in the radial direction to define a gap, the gap extending in the axial direction from the internal cavity;
• a seal arranged in the gap, the seal extending between the axial portion of the support structure and the outer portion to block the gap;
• a first flange formed in the outer portion, the first flange extending in the radial direction into the gap from the outer portion towards the axial portion of the support structure to establish a tortuous flow path, the first flange configured to partially block the gap to define a first section of the tortuous flow path;
• a second flange extending in the radial direction into the gap from the axial portion of the support structure towards the outer portion;
• and
• wherein the second flange extends into the gap at a position between the first flange and the radial portion of the support structure relative to the axial direction such that the second flange establishes a second section of the tortuous flow path, and the first and second sections are offset in the radial direction.