Floatwall Liner Projections for Jet Engine Combustor Cooling
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Solution Overview
Problem
The thermal environment of a jet engine combustor poses challenges in designing a cooling scheme that minimizes the use of cooling air, reduces maximum temperature, and mitigates temperature gradients, while conventional impingement film-cooled floatwalls are inefficient in managing high temperatures and temperature variations.
Innovation Solution
A liner with an array of projections, such as pin-fins, is used on the panel to enhance cooling, with varying densities of impingement and effusion cooling holes distributed based on temperature zones to optimize heat transfer and uniformity.
Engineering Contradictions & Design Principles
Engineering Contradiction Analysis
1Reliability
If conventional impingement film-cooled floatwall is used, then the structure is simple, but the cooling efficiency is insufficient and temperature gradients are high
Solution Approach 1:
The patent applies local quality by varying the density of cooling holes (both impingement and effusion holes) across different zones of the panel. Areas prone to higher temperatures have greater hole density, while cooler areas have lower density. This non-uniform distribution optimizes cooling efficiency in hot spots without unnecessarily complicating the entire structure.
Solution Approach 2:
The patent introduces a new dimension to the cooling structure by adding protrusions (such as pins or ribs) on the backside of the panel. These protrusions create additional cooling surfaces and improve heat transfer in a direction perpendicular to the panel surface, enhancing cooling efficiency without significantly increasing in-plane structural complexity.
2Use of energy by moving object
If cooling air usage is reduced, then energy consumption decreases, but temperature control becomes more difficult
Solution Approach 1:
The patent changes the physical parameters of the cooling system by modifying the hole density distribution and adding backside protrusions. These parameter changes improve heat transfer efficiency, allowing better temperature control with reduced cooling air consumption. The varied hole density optimizes the cooling effect in different thermal zones.
Solution Approach 2:
The patent creates a composite cooling structure by combining the panel front side with impingement/effusion holes and the back side with protrusions. This composite approach enhances overall heat transfer performance, enabling effective temperature control with less cooling air by utilizing multiple heat transfer pathways.
3Stability of the object's composition
If uniform cooling is achieved, then temperature gradients are reduced, but cooling air consumption increases
Solution Approach 1:
The patent applies local quality by implementing zone-based hole density variation. Areas prone to higher temperatures have higher hole density for intensified cooling, while cooler areas have lower density. This localized approach achieves temperature uniformity across the panel without requiring excessive cooling air throughout the entire structure.
Solution Approach 2:
The patent applies partial action by concentrating cooling effort where it is most needed (in high-temperature zones) rather than uniformly across the entire panel. The varied hole density ensures sufficient cooling in critical areas without wasting cooling air in already-cool regions, achieving temperature uniformity with optimized air consumption.
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 enhances heat transfer by approximately 50% compared to conventional cooling methods, improving the reliability and durability of combustor hardware while reducing cooling air usage and temperature gradients.
Implementation Method 1
an array of projections configured to enhance a cooling of the panel
Implementation Method 2
enhance heat transfer by approximately 50% compared to conventional cooling methods
Implementation Method 3
the shell comprises a plurality of impingement cooling holes
Implementation Method 4
the panel includes a plurality of effusion cooling holes
Data Source
AI summary
A liner associated with an engine of an aircraft is described. The liner includes a panel and an array of projections configured to enhance a cooling of the panel and distributed on at least part of a first side of the panel that corresponds to a cold side of the panel.