Combustor Liner Resonator Thermal Barrier Coating
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Solution Overview
Problem
The application of thermal barrier coatings to gas turbine combustor liners can alter the damping performance of Helmholtz resonator assemblies, and existing masking techniques to protect these areas are impractical, leading to incomplete coating and increased risk of thermal fatigue due to exposure to hot combustion products.
Innovation Solution
The design incorporates resonator assemblies with slots in the inner plate and strategically applied masking material to allow for partial thermal barrier coating coverage, ensuring at least 50% of the inner surface is coated while minimizing the area left uncoated, thus protecting the liner from overheating.
Engineering Contradictions & Design Principles
Engineering Contradiction Analysis
1Temperature
If thermal barrier coating is applied to the entire inner surface of the liner, then thermal protection is improved, but the damping performance of resonator assemblies is altered
Solution Approach 1:
The patent applies thermal barrier coating selectively to specific regions of the liner inner surface using masking material. The coating is applied to areas away from the resonator assemblies while leaving the resonator areas uncoated, creating local quality differences that satisfy both thermal protection and damping performance requirements
2Reliability
If masking material is applied to protect resonator areas, then damping performance is preserved, but coating coverage is reduced leading to thermal exposure
Solution Approach 1:
The masking strategy creates local quality differences by applying coating only to specific regions. The unmasked areas around resonators preserve damping performance while masked areas provide thermal protection, resolving the contradiction through spatial differentiation
3Temperature
If cooling air flow is increased to protect liner from overheating, then thermal protection is improved, but energy consumption increases
Solution Approach 1:
The patent extracts the thermal protection function from the cooling air system by applying thermal barrier coating to the liner. This reduces the reliance on cooling air flow, thereby reducing energy consumption while maintaining thermal protection
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
This approach enhances the durability of combustor components by maintaining effective thermal protection while preserving the damping performance of resonator assemblies, reducing the risk of thermal fatigue and component failure.
Implementation Method 1
A thermal barrier coating is applied to a substantial portion of the inner surface of the liner to protect the liner from the hot combustion products passing therethrough
Implementation Method 2
One known method for controlling combustion acoustic pressure oscillations is to incorporate Helmholtz resonator assemblies into the liner. These resonator assemblies are commonly used to damp high frequency pressure oscillations in gas turbine combustor assemblies
Data Source
AI summary
A combustor assembly is provided comprising a combustor casing; a liner coupled to the combustor casing; a burner assembly coupled to the combustor casing; and at least one resonator assembly. The resonator assembly comprises a resonator outer plate having at least one opening, a resonator side wall coupled to the resonator outer plate, and a resonator inner plate defined by a portion of the liner. The resonator inner plate is coupled to the resonator side wall and has at least one slot formed therein having an aspect ratio of at least 4:1.