Vane arc segment with single-sided platform
A gas turbine engine includes a ceramic matrix composite (CMC) vane arc segments that are arranged in a circumferential row. Each of the CMC vane arc segments includes an airfoil section that defines first and second side walls, leading and trailing ends, and first and second radial ends. At the first radial end, the airfoil section has a single-sided platform that and the second side wall has a bearing surface. The single-sided platform of each of the CMC vane arc segments in the circumferential row is situated to bear against the bearing surface of the next of the CMC vane arc segments in the circumferential row.
1. A gas turbine engine comprising:
a plurality of ceramic matrix composite (CMC) vane arc segments arranged in a circumferential row, each of the CMC vane arc segments including
an airfoil section defining first and second side walls, leading and trailing ends, and first and second radial ends, the first and second side walls and leading and trailing ends defining an internal cavity,
wherein, at the first radial end, the airfoil section having a single-sided platform projecting in a circumferential direction from the first side wall and, also at the first radial end, the second side wall having a bulbous lobe defining a bearing surface, the bearing surface including a first facet and a second facet, the second facet overhanging the internal cavity, and
wherein the single-sided platform of each of the CMC vane arc segments in the circumferential row, the single-sided platform including an edge that has a hooked tab, the hooked tab received over the bulbous lobe of the next, adjacent one of the CMC vane arc segments in the circumferential row such that the hooked tab overhangs into the internal cavity of the next, adjacent one of the CMC vane arc segments in the circumferential row and bears against second facet of the bearing surface of that next, adjacent one of the CMC vane arc segments in the circumferential row.
2. The gas turbine engine as recited in claim 1 , wherein the ledge has a window that opens to the internal cavity, the single-sided platform includes a circumferential side opposite the first side wall that has the hooked tab projecting there from, and the hooked tab of each of the CMC vane arc segments extends through the window, and bears against the second facet, of the next of the CMC vane arc segments in the circumferential row.
3. The gas turbine engine as recited in claim 1 , wherein the bearing surface includes a blind pin hole, the single-sided platform includes a platform pin hole, the platform pin hole of each of the CMC vane arc segments is radially aligned with the blind pin hole of the next of the CMC vane arc segments in the circumferential row, and there a lock pin that extends through the platform pin hole and the blind pin hole.
4. The gas turbine engine as recited in claim 1 , wherein CMC fiber plies from the second side wall divide to define a portion of the bearing surface and another portion of the bearing surface is formed by a filler material.
5. The gas turbine engine as recited in claim 1 , wherein the first side wall is a suction side wall and the second side wall is a pressure side wall.
6. The gas turbine engine as recited in claim 5 , wherein, at the second radial end, the airfoil section has an additional single-sided platform that projects from the first side wall in the circumferential direction away from the first side wall, and at the second radial end the second side wall has an additional bearing surface, and the additional single-sided platform of each of the CMC vane arc segments in the circumferential row is situated to bear against the additional bearing surface of the next of the CMC vane arc segments in the circumferential row.
7. The gas turbine engine as recited in claim 5 , wherein, at the second radial end, the airfoil section has an additional single-sided platform that projects from the second side wall in the circumferential direction away from the second side wall, and at the second radial end the first side wall has an additional bearing surface, and the additional single-sided platform of each of the CMC vane arc segments in the circumferential row is situated to bear against the additional bearing surface of the next of the CMC vane arc segments in the circumferential row.
8. The gas turbine engine as recited in claim 7 , wherein the seals are, respectively, radially opposite the bearing surface of each of the CMC vane arc segments.
9. The gas turbine engine as recited in claim 1 , further comprising a static support that supports the CMC vane arc segments and seals that are disposed, respectively, between the static support and the single-sided platform of each of the CMC vane arc segments.
10. The gas turbine engine as recited in claim 1 , wherein the CMC vane arc segments are formed of silicon carbide fibers disposed in a silicon carbide matrix.
11. The gas turbine engine as recited in claim 1 , further comprising a compressor section, a combustor in fluid communication with the compressor section, and a turbine section in fluid communication with the combustor, wherein the CMC vane arc segments are in the turbine section.
12. The gas turbine engine as recited in claim 1 , wherein, at the first radial end, the second side wall includes a ledge that borders the bearing surface, and the single-sided platform of each of the CMC vane arc segments in the circumferential row is situated to bear against the ledge of the next of the CMC vane arc segments in the circumferential row.
13. The gas turbine engine as recited in claim 1 , wherein both the first facet and the second facet are radially-outwardly-facing surfaces.
14. The gas turbine engine as recited in claim 1 , wherein, at the second radial end, the airfoil section has an additional single-sided platform that projects from the first side wall in an opposite circumferential direction from the single-sided platform at the first radial end, and at the second radial end the second side wall has an additional bearing surface, and the additional single-sided platform of each of the CMC vane arc segments in the circumferential row is situated to bear against the additional bearing surface of the next of the CMC vane arc segments in the circumferential row.
15. A method of assembly, comprising:
providing a plurality of ceramic matrix composite (CMC) vane arc segments, each of the CMC vane arc segments includes an airfoil section that defines first and second side walls, leading and trailing ends, and first and second radial ends, the first and second side walls and leading and trailing ends define an internal cavity, at the first radial end the airfoil section has a single-sided platform that projects from the first side wall in a circumferential direction away from the airfoil section, the single-sided platform including an edge that has a hooked tab, and the second side wall has a bulbous lobe defining a bearing surface that includes a first facet and a second facet, and the second facet overhangs the internal cavity, and;
positioning the CMC vane arc segments at circumferentially-spaced apart radial positions in a circumferential row about a central axis; and
moving the CMC vane arc segments radially inwardly toward the central axis from the circumferentially-spaced apart radial positions to final radial positions, wherein during the moving the CMC vane arc segments move toward one another such that the hooked tab of each single-sided platform of each of the CMC vane arc segments comes to bear against the first facet and the second facet of the bearing surface of the next of the CMC vane arc segments in the circumferential row.
16. The method as recited in claim 15 , wherein the CMC vane arc segments are pre-loaded with a pre-stress, and the pre-stress is released after the moving to the final radial position.