Segmented Ceramic Topcoat for Gas Turbine Stress Relief
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Solution Overview
Problem
Protective coatings in gas turbine engines, such as abradable ceramic coatings on blade outer air seals, are prone to erosion and spalling due to internal stresses, leading to reduced longevity and the need for frequent replacement.
Innovation Solution
A thermally insulating topcoat with microstructural discontinuities, or faults, is applied over a bond coating with a step feature, which reduces internal stresses by providing planes of weakness and allowing for thermal expansion without cracking, using a ceramic material over a metal alloy substrate.
Engineering Contradictions & Design Principles
Engineering Contradiction Analysis
1Temperature
If a continuous thermally insulating topcoat is applied over the bond coating, then thermal insulation performance is improved, but internal stresses cause erosion and spalling reducing coating longevity
Solution Approach 1:
The continuous topcoat is segmented into discrete segments separated by gaps or faults. These segments are spaced apart to allow differential thermal expansion and stress relief, preventing the buildup of internal stresses that lead to erosion and spalling. The segmentation maintains thermal insulation functionality while improving coating durability through stress management.
2Reliability
If the topcoat is segmented with faults, then coating longevity is improved by reducing stress-related erosion, but thermal insulation performance may be reduced due to discontinuities
Solution Approach 1:
The topcoat transitions from a uniform continuous structure to a non-uniform segmented structure with varying local properties. The segments maintain insulation characteristics while the gaps provide stress relief. This local variation in structure optimizes both durability and thermal performance by placing insulation material where needed while allowing stress accommodation.
3Reliability
If a step feature is added to the bond coating or substrate, then stress distribution is improved allowing for thermal expansion, but manufacturing complexity increases
Solution Approach 1:
The step feature is pre-formed in the bond coating or substrate before applying the topcoat segments. This preliminary structuring creates predetermined stress relief zones that guide the segmentation pattern of the topcoat. By establishing the stress management architecture early in the manufacturing process, the subsequent topcoat application becomes more straightforward and reliable.
Applied Scientific Principles
This section explains which scientific principles are used to turn an abstract innovation direction into a practical engineering solution.
Function Achieved in This Case
The solution extends the lifespan of protective coatings by mitigating stress-related issues, reducing the likelihood of delamination and cracking, and enhancing the thermal insulation of gas turbine engine components.
Implementation Method 1
A thermally insulating topcoat is disposed on the bond coating
Implementation Method 2
The thermally insulating topcoat includes a first topcoat portion separated by at least one fault that extends through the thermally insulating topcoat from a second topcoat portion
Data Source
AI summary
A gas turbine engine article includes a substrate and a bond coating that covers at least a portion of the substrate with a step formed in at least one of the substrate and the bond coating. A thermally insulating topcoat is disposed on the bond coating. The thermally insulating topcoat includes a first topcoat portion separated by at least one fault that extends through the thermally insulating topcoat from a second topcoat portion.


