Oxide Coatings in Aero-Turbine Engines
Abstract
Oxide coatings used for various components in the hot section of aero-turbine engines experience temperature gradients at various stages during their flight cycle. One gradient exists during steady-state, due to the combination of the combustion environment next to the free surface and internal cooling of the underlying superalloy substrate. Other gradients develop during cooling of the surface when engine power is reduced. It is argued that deep delaminations, when observed within the oxide layer, can only be explained by the presence of a significant stress gradient in the coating, governed by these thermal circumstances. Two extreme cool-down scenarios are addressed. In one, the surface is cooled suddenly to a lower temperature, followed by slow uniform cooling. In the other, the entire system reduces its temperature uniformly before the temperature gradient in the TBC is eliminated. Criteria for guarding against delaminations within the oxide layer and along the interface with the substrate are provided and the outcome visualized in the form of delamination maps. A comparison with engine experience has provided a preliminary assessment of the relevant thermal scenarios.
Document Details
- Document Type
- Technical Report
- Publication Date
- Feb 28, 2008
- Accession Number
- ADA479151
Entities
People
- Anthony G. Evans
- John W. Hutchinson
Organizations
- University of California, Santa Barbara