Abradable Coating Deposition on CMC Shrouds
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Solution Overview
Problem
Gas turbine engine components, particularly ceramic matrix composite (CMC) shrouds and blades, face challenges with high-temperature durability and efficiency due to material mismatch and coating loss, leading to blade damage and reduced engine performance.
Innovation Solution
A method of depositing an abradable coating on CMC components using a slurry mixture with bi-modal ceramic particulate and sintering aids, which forms a porous layer that breaks away upon contact, reducing blade damage and improving material utilization.
Engineering Contradictions & Design Principles
Engineering Contradiction Analysis
1Reliability
If plasma spray process is used to deposit abradable coating, then coating can be applied to CMC shroud, but material utilization is poor with only small fraction of sprayed material comprising the coating
Solution Approach 1:
The patent replaces the plasma spray mechanical deposition system with a chemical solution-based dip coating system. The slurry containing ceramic particulates and sol-gel precursors is immersed onto the CMC shroud, allowing complete material utilization without the waste inherent in spray processes. The chemical bonding mechanism through sol-gel transformation ensures reliable coating adhesion without requiring high-energy plasma fields.
Solution Approach 2:
The patent changes the deposition parameters from high-energy plasma spray to low-energy dip coating followed by controlled thermal processing. The slurry is applied at room or elevated temperatures, then dried and sintered in a controlled atmosphere furnace. This parameter change transforms the deposition mechanism from mechanical impact to chemical precipitation and thermal consolidation, improving material efficiency.
2Reliability
If abradable coating is patterned using metal mask to form ridges, then blade rub protection is improved, but material utilization is further reduced
Solution Approach 1:
The patent applies preliminary patterning to the CMC shroud surface before coating deposition. Ridges or grooves are pre-formed on the shroud, and the slurry is then dip-coated over these features. The metal mask is eliminated because the substrate geometry itself provides the pattern template, preventing material waste from mask coverage areas while still creating the desired ridge structure for blade rub protection.
Solution Approach 2:
The patent extracts and eliminates the metal mask component from the coating process. Instead of using a mask to define the ridge pattern, the shroud surface is pre-formed with the desired geometry, and the coating slurry conformally deposits over these features. This removes the material waste associated with masking areas that receive no coating.
3Temperature
If CMC shroud material (silicon carbide) is used, then high temperature capability and light weight are achieved, but blade damage risk increases due to harder material
Solution Approach 1:
The patent creates a composite structure by depositing a ceramic-based abradable coating onto the CMC shroud. The coating comprises ceramic particulates (such as alumina, silica, or rare earth oxides) bound with a glassy matrix formed from sol-gel precursors. This composite coating is softer than the CMC substrate, providing a sacrificial layer that protects the harder CMC shroud from damaging blade contact while maintaining the shroud's high-temperature capability.
Solution Approach 2:
The patent creates a porous abradable coating structure through controlled sintering of the sol-gel derived ceramic material. The porous structure, with controlled porosity and interconnected voids, allows the coating to be more compliant and easier to abrade compared to dense CMC material. When blade contact occurs, the porous structure collapses and erodes preferentially, protecting the underlying CMC shroud from damage.
4Ease of manufacture
If conventional coating methods are used, then coating can be applied, but coating loss occurs leading to reduced durability
Solution Approach 1:
The patent replaces mechanical plasma spray deposition with chemical sol-gel based dip coating. The slurry is immersed onto the CMC shroud and then undergoes controlled drying and sintering. The chemical bonding mechanisms through sol-gel transformation and sintering create strong adhesion to the CMC substrate, preventing coating loss that plagues mechanically applied coatings while maintaining manufacturing simplicity.
Solution Approach 2:
The patent utilizes phase transitions in the sol-gel process to ensure durable coating formation. The organic precursors in the slurry undergo hydrolysis and condensation to form an inorganic gel network, which then dries to a xerogel state, and finally sinters to a dense ceramic structure. These controlled phase transitions create strong chemical bonds between the coating and CMC substrate, preventing coating delamination and loss during service.
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 abradable coating effectively inhibits blade damage by breaking away upon contact, enhancing the durability and efficiency of gas turbine engine components while minimizing material waste and optimizing the use of rare earth elements.
Implementation Method 1
The slurry may then be gelled to polymerize and crosslink forming a firm irreversible gel matrix on the gas turbine component
Implementation Method 2
The slurry may then be gelled to polymerize and crosslink forming a firm irreversible gel matrix on the gas turbine component
Implementation Method 3
The irreversible gel matrix is then dried to affect a particulate on the gas turbine engine component
Implementation Method 4
The particulate of said dried irreversible gel matrix on said gas turbine engine component is sintered forming a layer of the coating
Data Source
AI summary
A method of depositing abradable coating on an engine component is provided wherein the engine component is formed of ceramic matrix composite and one or more layers, including at least one environmental barrier coating, may be disposed on the outer layer of the CMC. An outermost layer of the structure may further comprise a porous abradable layer that is disposed on the environmental barrier coating and provides a breakable structure which inhibits blade damage. The abradable layer may be gel-cast on the component and sintered or may be direct written by extrusion process and subsequently sintered.