Combustor Dilution Hole Cooling Circuit
Find Innovative SolutionsGenerate Solutions
Solution Overview
Problem
Gas turbine combustors experience liner distress due to air jets in cross-flow, which disrupt cooling, increase heat transfer, and create biased distress patterns, primarily due to the interaction of air jets with the fuel-air mixture and the combustor liner materials, leading to oxidation and melting.
Innovation Solution
A cooling circuit is formed on the combustor panel or liner wall using a metal coating or plating over cooling channels, with an insert material that is subsequently removed, and post-processing techniques such as thermal barrier coating or electrodischarge machining to enhance cooling efficiency.
Engineering Contradictions & Design Principles
Engineering Contradiction Analysis
1Reliability
If air jets are introduced through dilution and trim holes to control combustion, then combustion spatial and temporal characteristics are improved, but liner distress (oxidation and melting) occurs due to disrupted cooling and increased heat transfer
Solution Approach 1:
The patent applies preliminary action by introducing cooling air through holes in the liner wall before the hot combustion gases reach critical temperatures. The cooling air is pre-positioned to counteract the heat transfer and prevent liner distress before oxidation and melting occur.
Solution Approach 2:
The patent uses cooling air as an intermediary substance introduced through dilution and trim holes. This cooling air acts as a mediator between the hot combustion gases and the liner wall, reducing heat transfer and preventing direct thermal damage to the liner material.
2Reliability
If air jets are used to tailor combustion, then emissions and performance are improved, but secondary flows and vortical structures disrupt cooling and drive hot gases to liner surfaces
Solution Approach 1:
The patent applies local quality by introducing cooling air at specific locations through holes in the liner wall where hot gases are driven by secondary flows. The cooling is localized to the areas most affected by vortical structures and secondary flows, targeting specific hot spots on the liner surface.
Solution Approach 2:
The cooling air is introduced in advance to counteract the temperature increase caused by secondary flows and vortical structures before hot gases can drive the liner surface temperature to dangerous levels.
3Quantity of substance
If dilution holes are present to provide feed air, then combustion support is improved, but flow acceleration around holes increases heat transfer and strengthens secondary flows
Solution Approach 1:
The patent introduces cooling air through the same dilution and trim holes used for combustion support. This cooling air acts as an intermediary that reduces heat transfer to the liner wall, counteracting the increased heat transfer caused by flow acceleration around the holes.
Solution Approach 2:
The patent changes the parameters of the air flow through dilution holes by introducing cooling air that modifies the temperature and velocity profiles. This parameter change reduces the heat transfer to the liner wall while maintaining the necessary feed air quantity for combustion.
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 effectively reduces liner distress by improving cooling efficiency and preventing oxidation, thereby extending the lifespan of combustor components and maintaining performance.
Implementation Method 1
A cooling circuit is formed on the combustor panel or liner wall
Implementation Method 2
cooling channels with an insert material that is subsequently removed
Implementation Method 3
post-processing techniques such as thermal barrier coating
Data Source
Figure 1A
Figure 1B
Figure 2
AI summary
Method 300A for forming a cooling circuit in at least one of a combustor panel or liner wall of an aircraft engine. The method includes producing 302A a substrate with the cooling circuit formed in the substrate, where the cooling circuit is located in proximity to an aperture associated with the at least one of a panel or liner wall.