Gas Turbine Combustor Cooling Liner Recesses
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Solution Overview
Problem
Existing gas turbine combustors face challenges in maintaining cooling performance while minimizing pressure loss and structural intensity, particularly in high-temperature zones, which affects product reliability and efficiency.
Innovation Solution
A gas turbine combustor design featuring a combustion liner with circularity recesses on its outer peripheral side, forming a convex surface at a right angle to the flow direction, allowing for enhanced heat transfer and reduced pressure loss through accelerated flow velocity and vortex generation, eliminating the need for overlapping metal structures.
Engineering Contradictions & Design Principles
Engineering Contradiction Analysis
1Temperature
If conventional cooling structures are used in high-temperature zones, then cooling performance is maintained, but pressure loss increases and structural intensity deteriorates
Solution Approach 1:
The patent applies local quality by forming convex portions only in high-temperature zones where cooling is most needed. The convex portions are strategically positioned on the combustion liner outer peripheral surface in regions exposed to highest thermal loads, while other areas maintain smooth surfaces to minimize flow resistance and pressure loss.
Solution Approach 2:
The patent transitions from two-dimensional flat liner surfaces to three-dimensional convex structures. These convex portions protrude from the liner surface into the cooling medium flow path, creating additional heat transfer surface area and inducing vortex flow patterns that enhance cooling efficiency without significantly increasing pressure loss.
2Temperature
If conventional cooling structures are used in high-temperature zones, then cooling performance is maintained, but structural intensity deteriorates
Solution Approach 1:
The convex portions are localized to high-temperature zones rather than covering the entire liner surface. This targeted approach provides enhanced cooling where thermally demanded while preserving the structural integrity and smooth load distribution of the liner in other regions, avoiding the structural weakening that would result from extensive rib or fin structures.
3Temperature
If overlapping metal structures are used for cooling enhancement, then cooling performance improves, but device complexity and manufacturing difficulty increase
Solution Approach 1:
The patent extracts the cooling enhancement function from separate overlapping metal structures (such as ribs or fins that would require assembly) and integrates it directly into the combustion liner body through convex portions formed as integral features. This eliminates the need for additional components and simplifies manufacturing to a single-piece construction.
Solution Approach 2:
The cooling enhancement features are merged with the combustion liner structure itself. The convex portions are formed as integral parts of the liner during manufacturing, combining the structural and cooling functions into a single component, thereby reducing device complexity and eliminating assembly requirements for separate cooling structures.
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 improves cooling performance, structural intensity, and reduces pressure loss, enhancing product reliability and service life while maintaining efficiency and low NOx emissions.
Implementation Method 1
In forced convection heat transfer, it is necessary to minimize an increase in pressure loss relative to heat-transfer enhancement
Implementation Method 2
circularity recesses, each having a surface forming a convex at a right angle with respect to a flowing direction of the heat-transfer medium
Data Source
Figure 1
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AI summary
There is provided a gas turbine combustor that achieves improved product reliability and a reduced increase in pressure loss through improvements made on a cooling characteristic and structural intensity. A gas turbine combustor structure includes a plurality of circularity recesses 20 formed on a side of an annular passage 11 on a partial area of a combustion liner 8 that requires cooling. The circularity recesses 20 each have a rectangular surface 25 forming a convex at a right angle with respect to a flowing direction of combustion air 2. The circularity recesses 20 is a rectangular triangle having an oblique surface 26 facing upstream of the flowing direction of the combustion air 2.