University of Central Florida Research Foundation Inc

Deutsches Zentrum Fur Luft-Und Raumfahrt E.v.

Seetha Raghavan

Quentin Fouliard

Ranajay Ghosh

Uwe Schulz

Ravisankar Naraparaju

Estefania Bohorquez

A phosphor thermometry device includes a laser that generates a laser pulse onto a thermal barrier coating (TBC) applied onto a substrate. A metallic bond coat layer is on the substrate. A ceramic top coat layer is on the bond coat layer and includes an undoped layer and a doped sensing layer having co-doped first and second rare-earth luminescent dopants that emit respective first and second different emission wavelengths upon excitation by the laser pulse. A detector receives reflected, convoluted luminescence signals from the TBC. First and second photomultiplier devices detect respective first and second different emission wavelengths of the convoluted luminescence signals. A controller receives and processes signals generated from respective first and second photomultiplier devices and determines luminescence lifetime decay and intensity variations for each of the respective first and second rare-earth luminescent dopants for temperature monitoring of the TBC.

Phosphor thermometry device for synchronized acquisition of luminescence lifetime decay and intensity on thermal barrier coatings

A thermal barrier coated component, such as a turbine blade formed from a superalloy substrate, includes a thermal barrier coating applied onto the substrate. A metallic bond coat layer is on the substrate and includes rare-earth luminescent dopants. A ceramic top coat layer is on the bond coat layer. A temperature sensing thermally grown oxide (TGO) layer is formed at the interface of the bond coat layer and ceramic top coat layer. The temperature sensing TGO layer includes grown rare-earth luminescent ions migrated from the metallic bond coat layer in an amount sufficient to enable luminescence sensing of the TGO layer for real-time phosphor thermometry temperature measurements at the TGO layer.

Method for forming a temperature sensing layer within a thermal barrier coating

Rare-earth doped thermal barrier coating bond coat for thermally grown oxide luminescence sensing

The present invention provides a non-destructive method of characterizing CMAS infiltration and CMAS assisted damage in thermal barrier coatings (TBCs). Such approach is especially relevant for determining the lifetime of coatings on e.g. turbines or parts of the turbines such as blades or in-liners of the combustion chambers. The turbines can be gas turbines or high-pressure turbines or others and may be stationary or used for example in aviation.

Non-destructive CMAS-infiltration characterization of thermal barrier coatings

Growing community of inventors

Orlando, FL, United States of America

Seetha Raghavan