Thermal barrier coating spallation detection system
First Claim
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1. A thermal barrier coating spallation detection system for a gas turbine engine, comprising:
- a hot gas path component installed within the gas turbine;
the hot gas path component comprising a phosphor layer and a thermal barrier coating applied over the phosphor layer;
a stimulant radiation source; and
an optical device;
wherein the optical device directs stimulant radiation at the thermal barrier coating and receives emission radiation; and
wherein a change in the received emission radiation caused by fluorescence of the phosphor layer indicates spallation of the thermal barrier coating.
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Abstract
The present application thus provides a thermal barrier coating spallation detection system for a gas turbine. The thermal barrier coating spallation detection system may include a hot gas path component with a phosphor layer and a thermal barrier coating, a stimulant radiation source, and an optical device such that the optical device directs stimulant radiation at the thermal barrier coating and receives emission radiation. A change in the received emission radiation indicates spallation of the thermal barrier coating.
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Citations
20 Claims
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1. A thermal barrier coating spallation detection system for a gas turbine engine, comprising:
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a hot gas path component installed within the gas turbine; the hot gas path component comprising a phosphor layer and a thermal barrier coating applied over the phosphor layer; a stimulant radiation source; and an optical device; wherein the optical device directs stimulant radiation at the thermal barrier coating and receives emission radiation; and wherein a change in the received emission radiation caused by fluorescence of the phosphor layer indicates spallation of the thermal barrier coating. - View Dependent Claims (2, 3, 4, 5, 6, 7, 8, 9, 10, 11, 12, 13, 14)
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15. A method of inspecting a thermal barrier coating with an underlying phosphor layer of a hot gas path component for spallation, comprising:
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emitting stimulant radiation at the thermal barrier coating; receiving emission radiation from the thermal barrier coating; comparing successive received emission radiation; and indicating spallation of the thermal barrier coating if a change is shown in the successive received emission radiation caused by fluorescence of the phosphor layer.
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16. A thermal barrier coating spallation detection system for a gas turbine engine, comprising:
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a hot gas path component installed within the gas turbine; the hot gas path component comprising a phosphor layer and a thermal barrier coating applied over the phosphor layer; a stimulant radiation source; an optical device; wherein the optical device directs stimulant radiation at the thermal barrier coating and receives emission radiation; and a digital camera in communication with the optical device; wherein a change in the received emission radiation displayed on the digital camera caused by fluorescence of the phosphor layer indicates spallation of the thermal barrier coating. - View Dependent Claims (17, 18, 19, 20)
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Specification