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Développement de barrière thermique céramique pour l'aéronautique

Abstract : The efficiency of thermal machines is thermodynamically limited by the maximum temperature that the materials can sustain. Most thermal barrier coatings in aero engines consist of an intermediate layer (MCrAIY) itself coated with an yttria stabilised zirconia (ZrO2) layer. But this system is limited to 1200°C. Above this temperature the microstructure is strongly influenced by sintering and phase modification, which leads to an abrupt degradation of the ceramic coating properties. This dissertation deals with the choice, elaboration and characterisation of ceramic materials that could lead to a temperature capability higher than 1350°C. ln this thesis, the study is limited to spinelles and perovskites materials. The thermo mechanical performances of the layers were iteratively improved thanks to the development of an image processing software for analysing the microstructure (porosity and cracks) related to the process parameter of the air plasma spray. The characterisation of physical properties such as phase stability, thermal extension, thermal conductivity, elasticity modules, hardness, thermal tests (static oxidation, resistance to temperature variation, engine test) and stress estimation allow the potential of the varioui ceramic coatings with new materials to be evaluated.
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Submitted on : Thursday, March 29, 2018 - 12:41:59 PM
Last modification on : Wednesday, March 24, 2021 - 10:24:03 AM

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  • HAL Id : tel-01750264, version 1



Regis Claude Lallement. Développement de barrière thermique céramique pour l'aéronautique. Autre [cond-mat.other]. Institut National Polytechnique de Lorraine, 2002. Français. ⟨NNT : 2002INPL011N⟩. ⟨tel-01750264⟩



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