TURBINE COMPONENT THERMAL BARRIER COATING WITH CRACK ISOLATING ENGINEERED SURFACE FEATURES

摘要

Thermal barrier coatings (TBCs) for turbine engine components are applied over engineered surface features (ESFs) that are formed in the component substrate or within intermediate layers applied between the substrate and the TBC. The ESFs help anchor the TBC layer and/or localize cracks that are bounded by one or more of the ESFs. During engine operation the ESFs arrest thermal stress-or foreign object damage (FOD)-induced crack propagation within the TBC that might otherwise allow excessive TBC spallation and subsequent thermal exposure damage to the turbine component underlying substrate. In some embodiments, the ESFs are combined with engineered groove features that are formed in the TBC.

主权项

1. A combustion turbine component having a heat insulating outer surface for exposure to combustion gas, comprising:
a metallic substrate having a substrate surface; an anchoring layer built upon the substrate surface; a thermally sprayed or vapor deposited or solution/suspension plasma sprayed thermal barrier coat (TBC), including at least an outer thermal barrier coat (OTBC) layer having an OTBC inner surface applied over and coupled to the anchoring layer and an OTBC outer surface for exposure to combustion gas; a planform pattern of engineered surface features (ESFs) projecting from the anchoring layer having projection height between approximately 2-75 percent of TBC layers aggregate total thickness; and a planform pattern of engineered groove features (EGFs) formed into and penetrating the previously applied OTBC layer through the OTBC outer surface, having a groove depth.