CPC F01D 11/005 (2013.01) [F01D 5/147 (2013.01); F01D 9/042 (2013.01); F05D 2240/12 (2013.01); F05D 2300/6033 (2013.01)] | 19 Claims |
1. An airfoil assembly for a gas turbine engine, comprising:
an outer portion including an airfoil section extending in a radial direction from a first platform section, the airfoil section including an internal cavity, and the outer portion comprising a ceramic material;
a support structure having a radial portion extending in the radial direction from an axial portion, and the radial portion received in the internal cavity such that a gap is established between the outer portion and the axial portion of the support structure, and the gap extending from the internal cavity; and
a flange extending in the radial direction from the first platform section of the outer portion such that the flange bounds the gap at a distance from the internal cavity;
wherein the gap includes an axial segment extending in an axial direction between the radial portion of the support structure and the first platform section, the flange is a raised protrusion extending outwardly from the first platform section at an intermediate position along the axial segment of the gap to establish a tortuous path, and the tortuous path has a lesser height along the raised protrusion than on either side of the raised protrusion.
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