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US 10,883,371 B1Granted
Ceramic matrix composite vane with trailing edge radial cooling
AssigneeROLLS-ROYCE plc
InventorsJames C. Smith, Emma C. Steedman, Michael J. Whittle, Edward M. Jones
Life of this patent
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Abstract
A component adapted for use in a gas turbine engine includes an aerofoil configured to interact with gases flowing through the gas turbine engine along a gas path. The aerofoil is formed to include a first passage that extends radially at least partway into the aerofoil and a second passage that extends radially into the aerofoil at a trailing edge of the aerofoil.
Claims20
A component for a gas turbine engine, the component comprising:
- a ceramic matrix composite aerofoil adapted to conduct gases flowing through a gas path of the gas turbine engine around the component during use of the component, the ceramic matrix composite aerofoil having a leading edge, a trailing edge spaced apart axially from the leading edge relative to an axis, a pressure side that extends between and interconnects the leading edge and the trailing edge, and a suction side that extends between and interconnects the leading edge and the trailing edge,
- the ceramic matrix composite aerofoil formed to define an aerofoil-shaped passage that extends radially at least partway into the ceramic matrix composite aerofoil, and
- the trailing edge, an aft portion of the pressure side, and an aft portion of the suction side of the ceramic matrix composite aerofoil define a trailing-edge passage that extends radially through the ceramic matrix composite aerofoil to conduct cooling fluid radially through the trailing edge of the ceramic matrix composite aerofoil.
A method comprising
- providing an aerofoil-shaped core preform that is formed to define an aerofoil-shaped passage that extends radially there through,
- providing a trailing edge filler preform that is formed to define a trailing-edge passage that extends radially there through,
- infiltrating the aerofoil-shaped core preform and the trailing edge filler preform together to provide a single, unitary ceramic matrix composite aerofoil component having the aerofoil-shaped passage and the trailing-edge passage, and
- directing a first portion of a cooling fluid radially through the aerofoil-shaped passage and directing a second portion of the cooling fluid radially through the trailing-edge passage.
1 more element
Dependencies are inferred from the claim text.