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US 2023/0021707 A1Published application
Turbine component with a thin interior partition
AssigneeRaytheon Technologies Corporation
InventorsDilip M. Shah, Alan D. Cetel, Venkatarama K. Seetharaman, Raymond Surace
Life of this patent
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Abstract
A hollow turbine airfoil or a hollow turbine casting including a cooling passage partition. The cooling passage partition is formed from a single crystal grain structure nickel based super alloy, a cobalt based super alloy, a nickel-aluminum based alloy, or a coated refractory metal.
Claims20
A method for fabricating a hollow turbine airfoil comprising:
- forming a cooling passage partition separately from the hollow turbine airfoil, the cooling passage partition comprising a cast sheet of a single crystal grain structure nickel based super alloy, the cast sheet of the single crystal grain structure nickel based super alloy having a single crystal grain structure direction parallel to a direction of solidification of the cast sheet of the single crystal grain structure nickel based super alloy;
- and
- positioning the cooling passage partition with respect to the hollow turbine airfoil.
A method for fabricating a hollow turbine casting comprising:
- forming a cooling passage partition separately from the hollow turbine casting, the cooling passage partition comprising a cast sheet of a single crystal grain structure nickel based super alloy, the cast sheet of the single crystal grain structure nickel based super alloy having a single crystal grain structure direction parallel to a direction of solidification of the cast sheet of the single crystal grain structure nickel based super alloy;
- and
- positioning the cooling passage partition with respect to the hollow turbine casting.
Dependencies are inferred from the claim text.