One-Piece Can Combustor Effusion Cooling Apertures
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Solution Overview
Problem
Gas turbines face performance and longevity issues due to extreme heating conditions in the combustion chamber, as existing cooling mechanisms are not adequately integrated into new turbine designs, and conventional combustors struggle to withstand high temperatures exceeding 800°C.
Innovation Solution
A one-piece can combustor design with a transition piece that includes a plurality of apertures for compressor discharge air to flow into the interior space, creating a flow annulus and utilizing effusion cooling to direct air jets for convective cooling, reducing heat transfer and extending the lifespan of turbine components.
Engineering Contradictions & Design Principles
Engineering Contradiction Analysis
1Productivity
If the turbine inlet temperature is raised to maximum efficiency, then the performance of the gas turbine is improved, but the combustion chamber temperature exceeds 800°C causing material failure
Solution Approach 1:
Cooling air is introduced through apertures in the transition piece before the hot combusted gases reach the turbine components, creating a protective cooling layer that prevents excessive heat buildup on the combustor surfaces
Solution Approach 2:
A cooling air layer acts as an intermediary between the hot combusted gases and the combustor components, transferring heat away from the materials and protecting them from thermal damage while allowing the turbine to operate at higher inlet temperatures
2Temperature
If conventional cooling mechanisms are used, then some cooling effect is achieved, but the cooling is not adequately integrated into new turbine designs
Solution Approach 1:
The cooling mechanism is merged with the transition piece structure itself, where the transition piece incorporates apertures that allow cooling air to pass through, combining the structural and cooling functions into a single integrated component
Solution Approach 2:
The transition piece serves multiple functions: it provides the structural transition from combustor to turbine, facilitates cooling air flow through its apertures, and directs the combusted gases, eliminating the need for separate cooling components
3Ease of manufacture
If apertures are oriented perpendicular to the surface, then cooling air flow is simple, but the cooling effectiveness is reduced
Solution Approach 1:
The apertures are oriented at specific angles rather than uniformly perpendicular, creating localized variations in cooling air flow direction that enhance the cooling effectiveness in different regions of the transition piece while maintaining manufacturability
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 provides enhanced cooling to turbine components by creating a convective cooling mechanism that prolongs heat transfer and reduces the temperature impact on the combustor, thereby improving the performance and longevity of gas turbines.
Implementation Method 1
effusion cooling to direct air jets for convective cooling
Implementation Method 2
creating a convective cooling mechanism that prolongs heat transfer
Data Source
Figure 1
Figure 2~3
AI summary
A combustor for an industrial turbine includes a single transition piece (120) transitioning directly from a combustor head-end (100) to a turbine inlet (16). The transition piece (120) includes an inner surface (300b) and an outer surface (300a). The inner surface bounds an interior space (304) for combusted gas flow from the combustor head-end (100) to the turbine inlet (16). The outer surface (300a) at least partially defines an area for compressor discharge air flow. The transition piece includes a plurality of apertures (200) configured to allow compressor discharge air flow into the interior space (304). Each of the plurality of apertures (200) extends from an entry portion on the outer surface (300a) to an exit portion (200b) on the inner surface (300b).