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 axial cooling channels in the trailing edge portion of the airfoil are arranged to permit axial flow of a cooling fluid from an interior of the turbine component at the trailing edge portion 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 trailing edge portion with axial cooling channels. The axial cooling channels are arranged to permit axial flow of a cooling fluid from an interior to 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 comprising a metal spar and a shell over the metal spar, the shell comprising a ceramic matrix composite material, the airfoil forming a leading edge, a trailing edge portion extending to a trailing edge, a suction side, and a pressure side opposite the suction side;
wherein a plurality of axial cooling channels in the trailing edge portion of the airfoil are arranged to permit axial flow of a cooling fluid through the trailing edge portion from an interior of the turbine component at the trailing edge portion to an exterior of the turbine component at the trailing edge portion, and
wherein at least one of the plurality of axial cooling channels makes a plurality of passes in an axial direction through the trailing edge portion.
2. The turbine component of claim 1 , wherein the at least one of the plurality of axial cooling channels exits the suction side or the pressure side of the trailing edge portion as a cooling film at a film cooling region.
3. The turbine component of claim 2 , wherein the film cooling region includes a plurality of film cooling holes directing the cooling film to form a boundary layer along an outer surface of the airfoil.
4. The turbine component of claim 1 , wherein at least a portion of the plurality of axial cooling channels are formed between layers of the ceramic matrix composite material.
5. The turbine component of claim 1 , wherein the plurality of axial cooling channels has a geometry extending radially through the airfoil selected from the group consisting of serpentine, zigzag, irregular, and combinations thereof.
6. The turbine component of claim 1 , wherein the plurality of axial cooling channels has a geometry extending axially through the airfoil selected from the group consisting of straight, wavy, zigzag, and irregular.
7. A method of making a turbine component comprising:
forming an airfoil, the airfoil comprising a metal spar and a shell over the metal spar, the shell comprising a ceramic matrix composite material, the airfoil having a leading edge, a trailing edge portion extending to a trailing edge, a suction side, a pressure side opposite the suction side, and a plurality of axial cooling channels in the trailing edge portion, the plurality of axial cooling channels being arranged to permit axial flow of a cooling fluid through the trailing edge portion from an interior of the turbine component at the trailing edge portion to an exterior of the turbine component at the trailing edge portion, thereby fluidly connecting the interior of the turbine component at the trailing edge portion with the exterior of the turbine component at the trailing edge portion;
wherein at least one of the plurality of axial cooling channels makes a plurality of passes in an axial direction through the trailing edge portion.
8. The method of claim 7 , wherein the forming comprises forming a film cooling region including at least one film cooling hole in the suction side or the pressure side in the trailing edge portion at an exit of at least one of the plurality of axial cooling channels.
9. The method of claim 7 , wherein the forming the airfoil further comprises forming the shell comprising the ceramic matrix composite material.
10. The method of claim 9 , wherein the forming the airfoil further comprises forming the metal spar, the shell being formed over the metal spar to form the airfoil.
11. The method of claim 7 , further comprising forming at least a portion of the plurality of axial cooling channels between layers of the ceramic matrix composite material.
12. The method of claim 7 , further comprising forming the plurality of axial cooling channels by machining the ceramic matrix composite material after formation of the ceramic matrix composite material.
13. The method of claim 7 , further comprising forming the ceramic matrix composite material to include a sacrificial material and burning or pyrolyzing out the sacrificial material either during or after forming the ceramic matrix composite material to form the plurality of axial cooling channels.
14. The method of claim 7 , wherein the plurality of axial cooling channels has a geometry extending axially through the airfoil selected from the group consisting of serpentine, zigzag, irregular, and combinations thereof.
15. 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 comprising a metal spar and a shell over the metal spar, the shell comprising a ceramic matrix composite material, the airfoil forming a leading edge, a trailing edge portion extending to a trailing edge, a suction side, and a pressure side opposite the suction side, the trailing edge portion having a plurality of axial cooling channels arranged to permit axial flow of the cooling fluid through the trailing edge portion from an interior of the turbine component at the trailing edge portion to an exterior of the turbine component at the trailing edge portion, wherein at least one of the plurality of axial cooling channels makes a plurality of passes in an axial direction through the trailing edge portion; and
directing the cooling fluid through the plurality of axial cooling channels through the trailing edge portion of the airfoil, each of the plurality of axial cooling channels fluidly connecting the interior of the turbine component at the trailing edge portion with the exterior of the turbine component at the trailing edge portion.
16. The method of claim 15 , wherein the directing further comprises directing the cooling fluid from at least one of the plurality of axial cooling channels through a film cooling hole in the suction side or the pressure side in the trailing edge portion.
17. The method of claim 15 further comprising operating a turbine comprising the turbine component.
18. The method of claim 15 , wherein each axial cooling channel of the plurality of axial cooling channels has a geometry extending axially through the airfoil selected from the group consisting of serpentine, zigzag, irregular, and combinations thereof.