Ceramic matrix composite vane with hybrid construction
AssigneeROLLS-ROYCE plc
InventorsAnthony G. Razzell, Michael J. Whittle, Ian M. Edmonds
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Abstract
A component for use in a gas turbine engine is made from ceramic materials. The component is made from a core preform containing ceramic reinforcement fibers. A plurality of preform tows are applied on at least a portion of the core preform and extend along at least a portion of the core preform to provide an outermost surface. The core preform and the plurality of preform tows are infiltrated with ceramic matrix material to form a ceramic matrix composite component.
Claims11
A method of forming a component for use in a gas turbine engine, the method comprising
- applying at least one ceramic ply around a mandrel to form an aerofoil shaped core preform that extends along a axis,
- covering at least a portion of the aerofoil shaped core preform with a plurality of ceramic reinforcement tow preforms that extend along the aerofoil shaped core preform to form an outermost surface and to provide a preform assembly,
- separating the aerofoil shaped core preform from the mandrel, and
- infiltrating the preform assembly with ceramic matrix material to provide a one-piece ceramic matrix composite aerofoil,
- further comprising transitioning the plurality of reinforcement tow preforms from the aerofoil shaped core preform radially outward from the axis to form at least a portion of an outer platform preform and at least a portion of an inner platform preform so that the aerofoil, the outer platform, and the inner platform provide a one-piece ceramic matrix composite vane after the preforms have been infiltrated with ceramic matrix material.
A method of forming a component for use in a gas turbine engine, the method comprising
- applying at least one ceramic ply around a mandrel to form an aerofoil shaped core preform that extends along a axis,
- covering at least a portion of the aerofoil shaped core preform with a plurality of ceramic reinforcement tow preforms that extend along the aerofoil shaped core preform to form an outermost surface and to provide a preform assembly,
- separating the aerofoil shaped core preform from the mandrel, and
- infiltrating the preform assembly with ceramic matrix material to provide a one-piece ceramic matrix composite aerofoil,
- further comprising providing a ceramic filler insert positioned radially between the aerofoil shaped core preform and the plurality of reinforcement tow preforms at a trailing edge of the ceramic matrix composite aerofoil.
Dependencies are inferred from the claim text.