Thermal Testing of High Performance: Thermal Barrier Coatings for Turbine Blades

L Bertamini; A Di Gianfrancesco

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NASA NTRS · 19950013265

Thermal Testing of High Performance: Thermal Barrier Coatings for Turbine Blades

L Bertamini·A Di Gianfrancesco

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Abstract

A 350 micron thick 7 wt.% Y 2 O 3 -ZrO 2 (7YSZ) ceramic Thermal Barrier Coating (TBC) was manufactured in an argon atmosphere and with a strictly controlled substrate temperature on flat IN 600 samples and on IN 100 aircraft turbine blades. This new atmosphere and temperature controlled spraying (ATCS) allows the reduction of the residual stresses and an improvement in the microstructure and in the mechanical properties of the coating. The good performance of these new TBC's was assessed in thermal fatigue and in thermal shock tests carried out in air at 1100°C and at 1280°C respectively. The oxidation rate of the metal-ceramic interface was measured at 1100°C. Failure of the TBC's was induced only by the deterioration (like oxidation, cracking, ...) of the uncoated parts of the samples, as testing temperature was too severe for the base metals. Spalling was thereafter driven by compressive stresses near the aluminum oxide layer at the metal-ceramic interface. The results of these tests underline the good quality of the ceramic coating manufactured by the new ATCS technology.

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L Bertamini, A Di Gianfrancesco. 1994-11-01. Thermal Testing of High Performance: Thermal Barrier Coatings for Turbine Blades. https://ntrs.nasa.gov/citations/19950013265

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