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US 10,329,950 B2Granted
Nozzle guide vane with composite heat shield
AssigneesRolls-Royce North American Technologies Inc., ROLLS-ROYCE plc
InventorsTed J. Freeman, Jeffrey A. Walston, Jun Shi, Tara G. Schetzel
Life of this patent
Estimating the term…
Abstract
A nozzle guide vane for a gas turbine engine is disclosed herein. The nozzle guide vane includes an inner endcap, an outer endcap, and at least one airfoil that extends from the inner endcap to the outer endcap. The nozzle guide vane further includes at least one composite heat shield component adapted to shield metallic components from high temperature gasses.
Claims20
A nozzle guide vane for a gas turbine engine, the nozzle guide vane comprising
- a metallic support structure including an inner endcap formed to include an inner attachment aperture and an outer endcap formed to include an outer attachment aperture, the outer endcap spaced from the inner endcap in a radial direction,
- an airfoil including an aerodynamic feature shaped to redirect gasses moving through a gas path between the inner end cap and the outer endcap, an inner attachment feature that extends from the aerodynamic feature into the inner attachment aperture of the inner endcap, and an outer attachment feature that extends from the aerodynamic feature into the outer attachment aperture of the outer endcap, and
- a ceramic-matrix composite heat shield system adapted to shield the metallic support structure from hot gasses moving through the gas path, the ceramic-matrix composite heat shield system including an inner heat shield arranged radially between the inner endcap and the gas path and an outer heat shield comprising ceramic-matrix composite materials arranged radially between the outer endcap and the gas path,
- wherein the inner heat shield is formed to include an inner locator aperture, the outer heat shield is formed to include an outer locator aperture, and the entire inner locator aperture and the entire outer locator aperture are smaller than the aerodynamic feature when the aerodynamic feature is viewed in the radial direction to overlap the heat shields with the aerodynamic feature, a cooling gap between the outer endcap and the outer heat shield.
1 more element
A gas turbine engine assembly, the assembly comprising
- a metallic support structure formed to include an attachment aperture,
- an airfoil including an aerodynamic feature shaped to interact with flow path gasses and an attachment feature that extends from the aerodynamic feature into the attachment aperture, the attachment feature fixed to the metallic support, and
- a ceramic-matrix composite heat shield arranged radially between the metallic support structure and the aerodynamic feature to shield the metallic support structure from hot gasses interacting with the aerodynamic feature,
- wherein the attachment feature extends through and engages a locator aperture formed in the ceramic-matrix composite heat shield to slide relative to the ceramic-matrix composite heat shield without interference and the locator aperture is smaller than the aerodynamic feature to overlap the ceramic-matrix composite heat shield such that the heat shield is held in place between the aerodynamic feature and the metallic support structure, and
- wherein a cooling gap is formed between the metallic support structure and the heat shield to provide cooling air to a backside of the heat shield.
2 more elements
A method for assembling a nozzle guide vane for a gas turbine engine, the method comprising
- providing an airfoil including an aerodynamic feature, an inner attachment feature that extends from the aerodynamic feature, and an outer attachment feature that extends from the aerodynamic feature,
- arranging inner and outer ceramic-matrix composite heat shields adjacent to the aerodynamic feature so that the inner attachment feature extends through and engages an inner locator aperture in the inner heat shield and the outer attachment feature extends through and engages an outer locator aperture in the outer heat shield to place the aerodynamic feature in contact with the inner and outer heat shields,
- arranging the airfoil adjacent to a metallic support structure so that the inner attachment feature extends into an inner attachment aperture of an inner endcap of the metallic support structure and the outer attachment feature extends into an outer attachment aperture of an outer endcap of the metallic support structure, wherein the inner locator aperture and the outer locator aperture is smaller than the aerodynamic feature to overlap the inner and outer ceramic-matrix composite heat shields with the aerodynamic feature and a cooling gap is formed between the outer endcap and the outer heat shield to provide cooling air to a backside of the outer heat shield, and
- securing the attachment features to the metallic support structure.
1 more element
Dependencies are inferred from the claim text.