Gas Turbine Combustor Welding Line Cooling via Film Air
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Solution Overview
Problem
Conventional gas turbine combustors face issues with insufficient cooling around the welding line, leading to increased metal temperatures and potential damage due to high combustion temperatures, as existing cooling methods do not effectively address this area.
Innovation Solution
A gas turbine combustor design that incorporates a cooling air hole in either the communication tube or the tubular member near the welding line, allowing cooling air to flow in a film-like fashion along the inner wall surface, blocking the welding line from direct exposure to high-temperature combustion gas, and a resonance device is positioned to avoid the welding line to enhance heat release to the casing interior.
Engineering Contradictions & Design Principles
Engineering Contradiction Analysis
1Reliability
If conventional cooling channels are used in the combustor basket, then the combustor can withstand high-temperature environment, but the periphery of the welding line is not sufficiently cooled and metal temperature increases causing cracks
Solution Approach 1:
The patent applies local quality by providing specialized cooling structures at the welding line periphery. Specifically, cooling channels are extended to the welding line area, and cooling air holes are provided in the communication tube at the connection position to the tubular member. This localized cooling approach ensures that the welding line periphery receives sufficient cooling air flow, preventing metal temperature increase while maintaining overall combustor reliability in high-temperature environment.
2Productivity
If combustion temperature is increased to improve efficiency, then energy efficiency improves, but the harsh environment damages the combustor structure
Solution Approach 1:
The patent uses cooling air as an intermediary substance to protect the combustor structure from the harsh high-temperature environment. Cooling air is introduced through cooling channels and cooling air holes, flowing along the inner wall surface in a film-like fashion to create a thermal barrier. This intermediary cooling air flow allows the combustor to withstand higher combustion temperatures for improved efficiency while preventing direct thermal damage to the structure.
3Temperature
If cooling air is introduced through existing channels, then overall cooling is achieved, but the welding line periphery remains under-cooled
Solution Approach 1:
The patent segments the cooling system into multiple functional parts: existing cooling channels for general cooling, cooling air holes specifically positioned at the communication tube connection position for welding line cooling, and film cooling along the inner wall surface. This segmentation allows each component to address specific cooling needs, ensuring uniform cooling distribution including the previously under-cooled welding line periphery.
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 effectively suppresses the increase in metal temperature around the welding line through film cooling, enhancing the reliability of the gas turbine combustor by maintaining lower temperatures and promoting heat release from the welding line area.
Implementation Method 1
the cooling air introduced from the casing interior space via the cooling air hole enters the interior space of the tubular member and flows downstream in the flow direction of the combustion gas along an inner wall surface of the tubular member in a film-like fashion
Implementation Method 2
the area of the tubular member around the welding line is directly exposed to the casing interior space. Compared to the case where the welding line is covered by the resonance device, heat release is promoted from the area of the tubular member around the welding line to the casing interior space
Data Source
AI summary
A gas turbine combustor is disposed in a casing interior space of a gas turbine. A combustor basket of the combustor is formed into a cylindrical shape by abutting ends of a curved panel member and welding the ends together along a welding line 16. A communication tube is provided for communication between an interior space of the combustor basket and an interior space of a combustor basket of an adjacent combustor. The position of the welding line of the combustor basket coincides with a connection position for connecting the communication tube to the combustor basket. A cooling air hole is disposed in the communication tube or in the combustor basket in the vicinity of the communication tube to introduce cooling air from the casing interior space 9 to the interior of the combustor basket.