Ceramic matrix composite turbine vane and method for making
AssigneesRolls-Royce High Temperature Composites Inc., Rolls-Royce North American Technologies Inc.
InventorsRobert J. Shinavski, Thomas Tran, Kevin Lukhard, Ted J. Freeman, Steffan Brown
Life of this patent
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Abstract
A turbine vane comprising ceramic matrix composite materials includes a vane support core, an airfoil, and an end wall that at least partially defines a gas path. The turbine vane is formed from a plurality of ceramic plies or preforms that are infiltrated with ceramic matrix material to form a one-piece ceramic matrix composite turbine vane.
Claims20
A turbine vane made from ceramic matrix composite materials and adapted for use in an aerospace gas turbine engine, the turbine vane comprising
- a vane support core arranged along an axis between a first end and a second end,
- an airfoil arranged radially outward from the vane support core relative to the axis and spaced apart axially from the first end and the second end of the vane support core, and
- a first end wall including (i) a core overwrap engaged with an outer surface of the vane support core and formed with a locking flange that flares radially outward away from the vane support core relative to the axis and (ii) a backing ply formed to include a cutout that receives the vane support core and the core overwrap and has an angled surface that engages with the locking flange of the core overwrap.
A bladed component made from ceramic matrix composite materials comprising
- a support core arranged along an axis from a first end to a second end of the support core and formed to include a hollow cavity that extends through the support core along the axis,
- an airfoil coupled with the support core radially outward from the support core with respect to the axis, and
- an end wall including a core overwrap that overwraps the support core and a backing ply arranged generally perpendicular to the axis,
- wherein the core overwrap includes an axially-inner flared end interlocked with the backing ply and engaged with an angled inner surface of a cutout formed in the backing ply such that the end wall is blocked from axial movement relative to the support core by the core overwrap.
A method of constructing a turbine vane adapted for used in an aerospace gas turbine engine with a central rotation axis, the method comprising
- providing a vane support core that extends along an axis between a first end of the vane support core and a second end of the vane support core,
- coupling an end wall to the vane support core between the first end of the vane support core and the second end of the vane support core, the end wall including a backing ply including a cutout having an angled inner surface and a core overwrap adjacent to the backing ply and overwrapping the vane support core,
- flaring an axially-inner end of the core overwrap radially outward away from the vane support core, and
- interlocking the axially-inner end of the core overwrap in the cutout of the backing ply such that the flared axially-inner end engages the angled inner surface so as to block movement of the end wall in an axial direction relative to the vane support core.
Dependencies are inferred from the claim text.