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US 10,329,917 B2Granted
Gas turbine engine component external surface micro-channel cooling
AssigneeUnited Technologies Corporation
InventorJohn Quitter
Life of this patent
Estimating the term…
Abstract
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.
Claims20
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.
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.
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.
Dependencies are inferred from the claim text.