Vane arc segment with single-sided platform
AssigneeRtx Corporation
InventorChristian X. Campbell
Life of this patent
Estimating the term…
Abstract
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.
Claims16
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.
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.
Dependencies are inferred from the claim text.