Method and system for enhancing heat transfer of turbine engine components
A method and system for enhancing the heat transfer of turbine engine components is disclosed that includes applying a metallic coating having a high thermal conductivity to the cold side of a turbine component to enhance heat transfer away from the component. The metallic coating may be roughened to improve heat transfer. The metal coating may be a Ni—Al bond coating having an aluminum content greater than about 50 weight percent.
1. A turbine combustion component, comprising:
a substrate having a hot side surface and a cold side surface, the cold side surface being an outside surface;
a bond coat overlying the substrate hot side surface; and
a thermal barrier coating overlying the bond coat;
wherein the cold side surface of the substrate has a metallic layer having a high thermal conductivity, the metallic layer:
having a surface roughness of between about 300 and about 900 micro-inches;
comprising a NiAl phase; and
having greater than about 50 weight percent aluminum.
2. The component of claim 1 , wherein the high thermal conductivity is between about 20 and about 60 BTU/hr ft ° F.
3. The component of claim 1 , wherein the substrate is a NiAl greater than about 50 weight percent aluminum having a substrate high thermal conductivity.
4. The component of claim 1 , wherein the thermal barrier coating comprises a ceramic layer deposited on and in contact with the bond coat.
5. The component of claim 1 , wherein the component further comprises:
a bond coat deposited on and in contact with the hot side surface; and
a ceramic layer deposited on and in contact with the bond coat;
wherein the outside surface is a surface of the metallic layer deposited on and in contact with the cold side surface.
6. The component of claim 5 , wherein the metallic layer has a thickness of between about 50 μm and about 600 μm.
7. The system of claim 1 , wherein the roughness is applied in the form of dimples.
8. The system of claim 1 , wherein the roughness is applied in the form of grooves.
9. The system of claim 1 , wherein the outer surface is additionally roughened after the deposition of a second bond coat by a mechanical process.
10. The system of claim 1 , wherein the outer surface is additionally roughened after the deposition of a second bond coat by a chemical roughening process.
11. A thermal barrier coating system for a substrate, comprising:
a bond coat deposited on and in contact with a hot side surface of the substrate;
a ceramic layer deposited on and in contact with the bond coat; and
an outside surface having a high thermal conductivity greater than a thermal conductivity of the hot side surface;
wherein the outside surface is a surface of a metallic layer, the metallic layer:
consisting essentially of a NiAl phase; and
comprising greater than about 50 weight percent aluminum; and
wherein the outside surface has a roughness of between about 300 and about 900 micro-inches.
12. The system of claim 11 , wherein the high thermal conductivity is between about 20 and about 60 BTU/hr ft ° F.
13. The system of claim 11 , wherein the metallic layer has a thickness of about 50 μm to about 600 μm.
14. A turbine combustion component, comprising:
a substrate having a hot side surface and a cold side surface;
an outside surface having a high thermal conductivity greater than a thermal conductivity of the hot side surface;
wherein:
the outside surface is a surface of a metallic layer, the metallic layer:
consisting essentially of a NiAl phase; and
comprising greater than about 50 weight percent aluminum;
the high thermal conductivity is between about 20 and about 60 BTU/hr ft ° F.; and
the outside surface has a roughness of between about 300 and about 900 micro-inches.
15. A method of improving the heat transfer of a component, comprising:
providing a substrate having:
a hot side surface and a cold side surface;
a bond coat overlying the hot side surface; and
a thermal barrier coating overlying the bond coat; and
depositing a metallic layer having a high thermal conductivity on and in contact with the cold side surface;
wherein the metallic layer:
has a surface roughness of between about 300 and about 900 micro-inches;
comprises a NiAl phase; and
has greater than about 50 weight percent aluminum.
16. The method of claim 15 , wherein the high thermal conductivity is between about 20 and about 60 BTU/hr ft ° F.
17. The method of claim 15 , wherein the thermal barrier coating comprises a ceramic layer deposited on and in contact with the bond coat.
18. The method of claim 15 , wherein the metallic layer has a thickness of between about 50 μm and about 600 μm.
19. The method of claim 15 , wherein the roughness is applied in the form of dimples.
20. The method of claim 15 , wherein the roughness is applied in the form of grooves.