Thermal barrier coating systems including a rare earth...

C - Chemistry – Metallurgy – 23 – C

Patent

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C23C 4/08 (2006.01)

Patent

CA 2709930

Thermal barrier coating systems for use with hot section components of a gas turbine engine include an inner layer overlying a bond coated substrate and a top layer overlying at least a portion of the inner layer. The inner layer includes a thermal barrier material such as yttria-stabilized zirconia. The top layer includes a rare earth aluminate. The thicknesses and microstructures of the layers may be varied depending on the type of component to be coated. Articles incorporating the thermal barrier coating system exhibit improved resistance to CMAS infiltration

L'invention concerne des systèmes de revêtement de barrière thermique utilisés avec des composants de la section chaude d'un moteur de turbine à gaz, comprenant une barrière interne recouvrant un substrat de liaison revêtu et une couche supérieure recouvrant au moins une partie de la couche interne. La couche interne comprend un matériau de barrière thermique tel que du zirconium stabilisé à l'yttrium. La couche supérieure comprend un aluminate de terres rares. Les épaisseurs et les microstructures des couches peuvent varier en fonction du type de composant destiné à être revêtu. L'invention concerne également des articles incorporant ledit système de revêtement de barrière thermique, présentant une résistance à l'infiltration CMAS améliorée.

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