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US 2019/0293567 A1Published application
Non-destructive cmas-infiltration characterization of thermal barrier coatings
AssigneeDeutsches Zentrum für Luft- und Raumfahrt e.V.
InventorsRavisankar NARAPARAJU, Uwe SCHULZ, Seetha RAGHAVAN, Estefania BOHORQUEZ
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Abstract
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.
Claims16
A non-destructive method of characterizing CMAS-infiltration in barrier coatings comprising:
- i. providing a metallic substrate with a barrier coating after CMAS-infiltration,
- ii. analyzing the metallic substrate with Raman mapping, and
- iii. determining a concentration of any phase present in the barrier coating that undergoes a phase change initiated by CMAS-infiltration and that is detectable by a Raman technique.
Dependencies are inferred from the claim text.