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.
Turbine engine part coated in a thermal barrier, and a method of obtaining it
2022-10-11
Patent
Elektronische Ressource
Englisch
IPC: | B64C AEROPLANES , Flugzeuge / C04B Kalk , LIME / C23C Beschichten metallischer Werkstoffe , COATING METALLIC MATERIAL / C25D Verfahren für die elektrolytische oder elektrophoretische Herstellung von Überzügen , PROCESSES FOR THE ELECTROLYTIC OR ELECTROPHORETIC PRODUCTION OF COATINGS / F01D Strömungsmaschinen [Kraft- und Arbeitsmaschinen oder Kraftmaschinen], z.B. Dampfturbinen , NON-POSITIVE-DISPLACEMENT MACHINES OR ENGINES, e.g. STEAM TURBINES |
A TURBINE ENGINE PART COATED IN A THERMAL BARRIER, AND A METHOD OF OBTAINING IT
Europäisches Patentamt | 2019
|Effect of thermal barrier coated piston crown on engine characteristics
Tema Archiv | 2000
|Experimental Study of Energy Balance in Thermal Barrier Coated Diesel Engine
British Library Conference Proceedings | 2012
|Experimental Study of Energy Balance in Thermal Barrier Coated Diesel Engine
SAE Technical Papers | 2012
|