Turbine component and methods of making and cooling a turbine component
A turbine component includes a root and an airfoil extending from the root to a tip opposite the root. The airfoil forms a leading edge and a trailing edge portion extending to a trailing edge. A plurality of nested cooling channels in the trailing edge portion of the airfoil permit passage of a cooling fluid from an interior of the turbine component to an exterior of the turbine component at the trailing edge portion. A method of making a turbine component includes forming an airfoil having a leading edge, a trailing edge portion extending to a trailing edge, and a plurality of nested cooling channels in the trailing edge portion. Each nested cooling channel fluidly connects an interior of the turbine component with an exterior of the turbine component at the trailing edge portion. A method of cooling a turbine component is also disclosed.
1. A turbine component comprising:
a root; and
an airfoil extending from the root to a tip opposite the root, the airfoil forming a leading edge and a trailing edge portion extending to a trailing edge;
wherein a plurality of nested cooling channels in the trailing edge portion of the airfoil permit passage of a cooling fluid from an interior of the turbine component to an exterior of the turbine component at the trailing edge portion; and
wherein the airfoil comprises a first section and a second section, the first section and the second section being formed by metal three-dimensional printing and at least a portion of the plurality of nested cooling channels being formed at a surface of the first section or the second section.
2. The turbine component of claim 1 , wherein the airfoil is formed of a high-temperature superalloy.
3. The turbine component of claim 2 , wherein the second section is welded or brazed to the first section to form the airfoil.
4. The turbine component of claim 1 , wherein the plurality of nested cooling channels have a nested geometry selected from the group consisting of wavy, zigzag, serpentine, sinusoidal, irregular, and combinations thereof.
5. A method of making a turbine component comprising:
forming an airfoil having a leading edge, a trailing edge portion extending to a trailing edge, and a plurality of nested cooling channels in the trailing edge portion, each of the plurality of nested cooling channels fluidly connecting an interior of the turbine component with an exterior of the turbine component at the trailing edge portion;
wherein the forming comprises metal three-dimensionally printing a first section and a second section of the airfoil, at least a portion of the plurality of nested cooling channels being formed at a surface of the first section or the second section.
6. The method of claim 5 , wherein the metal three-dimensional printing comprises metal three-dimensional printing of a high-temperature superalloy to form the airfoil.
7. The method of claim 5 , wherein the forming further comprises welding or brazing the first section to the second section to form the airfoil.
8. The method of claim 5 , wherein the plurality of nested cooling channels have a geometry selected from the group consisting of wavy, zigzag, serpentine, sinusoidal, irregular, and combinations thereof.
9. A method of cooling a turbine component comprising:
supplying a cooling fluid to an interior of the turbine component, the turbine component comprising:
a root; and
an airfoil extending from the root to a tip opposite the root, the airfoil forming a leading edge and a trailing edge portion extending to a trailing edge, the trailing edge portion having a plurality of nested cooling channels; and
directing the cooling fluid through the plurality of nested cooling channels through the trailing edge portion of the airfoil, each of the plurality of nested cooling channels fluidly connecting the interior of the turbine component with an exterior of the turbine component at the trailing edge portion;
wherein the airfoil comprises a first section and a second section, the first section and the second section being formed by metal three-dimensional printing and at least a portion of the plurality of nested cooling channels being formed at a surface of the first section or the second section.
10. The method of claim 9 further comprising operating a turbine comprising the turbine component.
11. The method of claim 9 , wherein the airfoil is formed of a high-temperature superalloy.
12. The method of claim 11 , wherein the second section is welded or brazed to the first section to form the airfoil.
13. The method of claim 9 , wherein the plurality of nested cooling channels have a geometry selected from the group consisting of wavy, zigzag, serpentine, sinusoidal, irregular, and combinations thereof.