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.
Claims12
A hollow turbine airfoil comprising a 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;
- wherein the cooling passage partition is formed separately from the hollow turbine airfoil, has a maximum thickness of less than or equal to 8 mils (0.2 millimeters) and has bleed holes, a sinusoidal shape, raised features and holes, a helical configuration, or a combination thereof.
A hollow turbine casting comprising a 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;
- wherein the cooling passage partition is formed separately from the hollow turbine casting, has a maximum thickness of less than or equal to 8 mils (0.2 millimeters), and has bleed holes, a sinusoidal shape, or a combination thereof.
Dependencies are inferred from the claim text.