Gas turbine engine component external surface micro-channel cooling
A gas turbine engine component that includes a structure having a surface which includes multiple cooling channels having a width of 20-30 μm and a depth of 25-50 μm.
1. A gas turbine engine component comprising:
a structure having a surface, the surface including multiple cooling channels having a width of 20-30 μm and a depth of 25-50 μm, wherein the structure includes a substrate, a thermal barrier coating is adhered to the substrate with a bond coat having a uniform thickness, the thermal barrier coating providing the surface with the channels provided only in the thermal barrier coating such that the bond coat is arranged on a side of the thermal barrier coating opposite the channels, wherein the cooling channels are arranged in an intersecting pattern.
2. The gas turbine engine component according to claim 1 , wherein the surface is a line-of-sight surface.
3. The gas turbine engine component according to claim 1 , wherein the structure is an airfoil having an internal cooling passage.
4. The gas turbine engine component according to claim 1 , wherein the substrate is a nickel alloy, and the thermal barrier coating is a ceramic.
5. The gas turbine engine component according to claim 1 , wherein the cooling channels include a generally U-shaped cross-section.
6. The gas turbine engine component according to claim 1 , wherein the cooling channels include a generally V-shaped cross-section.
7. The gas turbine engine component according to claim 1 , wherein the cooling channels form pyramid shaped structures.
8. The gas turbine engine component according to claim 1 , wherein the cooling channels are arranged at acute angles relative to one another.
9. A gas turbine engine component comprising:
a structure having a surface, the surface including multiple cooling channels having a width of 20-30 μm and a depth of 25-50 μm, wherein the structure includes a substrate, a thermal barrier coating is adhered to the substrate with a bond coat having a uniform thickness, the thermal barrier coating providing the surface with the channels provided only in the thermal barrier coating such that the bond coat is arranged on a side of the thermal barrier coating opposite the channels, wherein the cooling channels are arranged in a circular pattern.
10. The gas turbine engine component according to claim 9 , wherein the surface is a line-of-sight surface.
11. The gas turbine engine component according to claim 9 , wherein the structure is an airfoil having an internal cooling passage.
12. The gas turbine engine component according to claim 9 , wherein the substrate is a nickel alloy, and the thermal barrier coating is a ceramic.
13. The gas turbine engine component according to claim 9 , wherein the cooling channels include a generally U-shaped cross-section.
14. The gas turbine engine component according to claim 9 , wherein the cooling channels include a generally V-shaped cross-section.
15. A gas turbine engine component comprising:
a structure having a surface, the surface including multiple cooling channels having a width of 20-30 μm and a depth of 25-50 μm, wherein the structure includes a substrate, a thermal barrier coating is adhered to the substrate with a bond coat having a uniform thickness, the thermal barrier coating providing the surface with the channels provided only in the thermal barrier coating such that the bond coat is arranged on a side of the thermal barrier coating opposite the channels, wherein the cooling channels provide a circular recess without circumscribing the structure.
16. The gas turbine engine component according to claim 15 , wherein the surface is a line-of-sight surface.
17. The gas turbine engine component according to claim 15 , wherein the structure is an airfoil having an internal cooling passage.
18. The gas turbine engine component according to claim 15 , wherein the substrate is a nickel alloy, and the thermal barrier coating is a ceramic.
19. The gas turbine engine component according to claim 15 , wherein the cooling channels include a generally U-shaped cross-section.
20. The gas turbine engine component according to claim 15 , wherein the cooling channels include a generally V-shaped cross-section.