Gas Turbine Combustor Panel Mounting with Seal Dividers
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Solution Overview
Problem
Gas turbine engine combustors face challenges in managing high operating temperatures, leading to oxidation, cracking, and thermal stresses in heat shields and panels, which traditional materials and cooling methods struggle to address effectively.
Innovation Solution
The implementation of a combustor design featuring high-temperature material panels secured by a panel mounting system with seal dividers and biasing elements, which allows for secure engagement and cooling of the panels, utilizing non-ductile materials like ceramic matrix composites and integrating cooling holes for efficient heat management.
Engineering Contradictions & Design Principles
Engineering Contradiction Analysis
1Temperature
If traditional cooling methods (convective, effusion, impingement) are used on heat shields, then cooling effect is achieved, but oxidation, cracking, and high thermal stresses occur leading to reduced reliability
Solution Approach 1:
The combustor wall is divided into multiple discrete panels (first panel, second panel, third panel, fourth panel) rather than a continuous structure. This segmentation allows each panel to be independently cooled and secured, distributing thermal stresses and improving overall reliability while maintaining effective cooling across the entire combustor wall.
Solution Approach 2:
The panels are designed with dynamic engagement features including biasing elements that apply continuous force to maintain panel contact with securing elements, and cooling air flow that dynamically adjusts to thermal conditions. This dynamic system adapts to thermal expansion and contraction, preventing cracking and maintaining reliability under varying temperature conditions.
2Productivity
If higher operating temperatures are used to extract more efficiency, then system efficiency improves, but difficulty in managing component temperatures increases
Solution Approach 1:
Different regions of the combustor wall are equipped with tailored cooling solutions. Each panel has its own cooling holes and is subjected to localized cooling air flow, allowing optimal temperature management in high-heat zones while maintaining overall system efficiency at higher operating temperatures.
Solution Approach 2:
The cooling system utilizes parameter changes in cooling air flow rate and temperature to manage panel temperatures. By adjusting these parameters, the system can operate at higher efficiency temperatures while actively controlling component temperatures to prevent material degradation.
3Temperature
If non-ductile high-temperature materials are used for panels, then resistance to high temperatures improves, but susceptibility to cracking and oxidation increases
Solution Approach 1:
The combustor wall utilizes composite construction with multiple panels made from high-temperature resistant materials. These composite panel structures, combined with the cooling system, provide both high-temperature resistance and protection against oxidation and cracking through the distributed cooling and securing mechanism.
Solution Approach 2:
The biasing elements and cooling system provide beforehand protection to the panels. The cooling air flow preemptively removes heat before it can cause thermal stress cracking, while the biasing elements maintain continuous contact to prevent gaps that could lead to oxidation, cushioning the panels against harmful environmental factors.
4Stability of the object's composition
If panels are securely engaged with securing elements, then structural stability improves, but complexity of mounting system increases
Solution Approach 1:
Multiple functions are merged into the mounting system components. The biasing elements simultaneously provide securing force, positioning, and thermal compensation. The cooling holes are integrated directly into the panels, eliminating separate cooling components. This merging reduces overall system complexity while maintaining structural stability.
Solution Approach 2:
The securing elements and biasing structures are designed with multi-functionality, serving both mechanical securing purposes and thermal management functions. This universal design approach stabilizes the panel structure without requiring additional dedicated components, thereby avoiding increased complexity.
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 design enhances the durability and efficiency of gas turbine engine combustors by allowing the use of non-ductile high-temperature materials, reducing thermal stresses, and enabling operation at higher temperatures while minimizing manufacturing complexities and maintenance costs.
Implementation Method 1
The seal divider biases the first and second high temperature material panels into secure engagement with the first and second securing elements
Implementation Method 2
the combustor shell includes at least one cooling hole located proximate each biasing element to provide cooling thereto
Data Source
Figure 1
Figure 2A
Figure 2B
AI summary
Combustors of gas turbine engines having a combustor shell (330; 430; 530; 630; 730; 830; 930; 1030) having a first end (342; 942) and a second end (344; 1044) opposite the first end, a first securing element (346; 946) positioned at the first end of the combustor shell, a second securing element (348; 1048) positioned at the second end of the combustor shell, a plurality of high temperature material panels (340; 440; 540; 640; 740; 840; 940; 1040) fixedly secured by the first securing element (346; 946) at the first end (342; 942) and the second securing element (348; 1048) at the second, wherein a panel gap (454; 554; 654) is formed between edges of adjacent high temperature material panels of the plurality of high temperature material panels, and a seal divider (450; 550; 650) extending from the first end (342; 942) to the second end (344; 1044) and positioned on the combustor shell and arranged to seal the panel gap (454; 554; 654) between adjacent first and second high temperature material panels.