A turbine engine part coated in at least a first ceramic layer forming a thermal barrier and including a ceramic material with first ceramic fibers dispersed in the first layer. The first layer may have a chemical composition gradient between a material for forming a thermal barrier and a material for providing protection against calcium and magnesium aluminosilicates, which is present at a greater content in an outer zone of the first layer, and/or the first layer may be porous and may present a porosity gradient such that an outer portion of the first layer presents lower porosity.
A TURBINE ENGINE PART COATED IN A THERMAL BARRIER, AND A METHOD OF OBTAINING IT
2019-08-22
Patent
Elektronische Ressource
Englisch
Turbine engine part coated in a thermal barrier, and a method of obtaining it
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