초록 ▼

A non-destructive method of detecting subsurface defects in thermal barrier coatings applied to gas turbine engine components is provided. In an exemplary embodiment, the method includes positioning a evanescent microwave microscope probe adjacent a turbine component surface coated with a thermal ba

A non-destructive method of detecting subsurface defects in thermal barrier coatings applied to gas turbine engine components is provided. In an exemplary embodiment, the method includes positioning a evanescent microwave microscope probe adjacent a turbine component surface coated with a thermal barrier coating, and scanning the thermal barrier coating by moving at least one of the evanescent microwave microscope probe and the component surface in relation to one another in an x-y plane while maintaining a predetermined distance between the probe and the thermal barrier coating constant.

대표청구항 ▼

1. A non-destructive method of detecting subsurface defects in thermal barrier coatings applied to gas turbine engine components, said method comprising:positioning an evanescent microwave microscope probe at a predetermined distance from a turbine component surface coated with a thermal barrier coa

1. A non-destructive method of detecting subsurface defects in thermal barrier coatings applied to gas turbine engine components, said method comprising:positioning an evanescent microwave microscope probe at a predetermined distance from a turbine component surface coated with a thermal barrier coating wherein the thermal barrier coating comprises an inner bond layer applied to a surface of the turbine component, an outer thermal insulating layer, and an intermediate layer;scanning the thermal barrier coating for compositional or microstructural variations in the thermal coating barrier by moving at least one of the evanescent microwave microscope probe and the component surface in an x-y plane while maintaining the predetermined distance between the probe and the thermal barrier coating constant; andcalculating at least one of the thermal conductivity of the thermal barrier coating and the quality of the thermal barrier coating at each scan point.2. A method in accordance with claim 1 wherein the evanescent microwave microscope probe comprises a metal probe tip having an end sharpened to a point and further comprises a conductive surface of at least one of silver, gold, platinum, palladium and alloys thereof, said positioning an evanescent microwave microscope probe adjacent a turbine component surface comprises positioning the sharpened probe tip a predetermined distance from the turbine component surface.3. A method in accordance with claim 2 wherein a detector is coupled to the evanescent microwave microscope probe, said method further comprising detecting reflected microwave radiation with the detector coupled to the evanescent microwave microscope probe.4. A method in accordance with claim 3 wherein the detector is coupled to a computer, said method further comprising sending detected reflected microwave radiation data to the computer.5. A method in accordance with claim 4 further comprising generating graphical plots from detected reflected microwave radiation data showing the morphology of the thermal barrier coating.6. A method in accordance with claim 1 wherein scanning the thermal barrier coating further comprises scanning an interface between the intermediate layer and the outer thermal insulating layer.7. A method in accordance with claim 1 wherein scanning the thermal barrier coating further comprises scanning an interface between the intermediate layer and the inner bond layer.8. A method in accordance with claim 1 wherein scanning the thermal barrier coating further comprises scanning an interface between the inner bond layer and the surface of the turbine component.9. A non-destructive method of detecting subsurface defects in thermal barrier coatings applied to gas turbine engine components utilizing an evanescent microwave microscope system comprising a probe, said method comprising:positioning an evanescent microwave microscope probe at a predetermined distance from a turbine component surface coated with a thermal barrier coating, the thermal barrier coating comprising an inner bond layer applied to a surface of the turbine component, an outer thermal insulating layer, and an intermediate layer;scanning the thermal barrier coating for compositional or microstructural variations in the thermal coating barrier by moving at least one of the evanescent microwave microscope probe and the component surface in relation to one another in an x-y plane while maintaining the predetermined distance between the probe and the thermal barrier coating constant;wherein the evanescent microwave microscope probe comprises a metal probe tip having an end sharpened to a point and further comprises a conductive surface of at least one of silver, gold, platinum, palladium and alloys thereof; andcalculating at least one of the thermal conductivity of the thermal barrier coating and the quality of the thermal barrier coating at each scan point.10. A method in accordance with claim 9 wherein the evanescent microwave microscope system further comprises a detector coupled to the evanescent microwave microscope probe, and said method further comprises detecting reflected microwave radiation with the detector coupled to the evanescent microwave microscope probe.11. A method in accordance with claim 10 wherein the evanescent microwave microscope system further comprises a computer coupled to the detector, and said method further comprises sending detected reflected microwave radiation data to the computer.12. A method in accordance with claim 11 further comprising generating graphical plots from detected reflected microwave radiation data showing the morphology of the thermal barrier coating.13. A method in accordance with claim 9 wherein scanning the thermal barrier coating further comprises scanning an interface between the intermediate layer and the outer thermal insulating layer.14. A method in accordance with claim 9 wherein scanning the thermal barrier coating further comprises scanning an interface between the intermediate layer and the inner bond layer.15. A method in accordance with claim 9 wherein scanning the thermal barrier coating further comprises scanning an interface between the inner bond layer and the surface of the turbine component.