Turbine Cooling Diffuser Section for Heat Transfer Efficiency
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Solution Overview
Problem
Existing gas turbine cooling systems are inefficient in transferring heat from internal structures to cooling air, requiring higher cooling air flow rates to achieve effective heat transfer, which affects the overall efficiency of the turbine.
Innovation Solution
The implementation of a cooling system that includes a component base with fluid supply passages, feed passages, delivery channels, and a diffuser section, where the cooling air is diffused before discharge onto the component surface, enhancing heat transfer efficiency.
Engineering Contradictions & Design Principles
Engineering Contradiction Analysis
1Ease of manufacture
If conventional microchannels are used without diffuser sections, then the structure is simple, but heat transfer efficiency is poor requiring higher cooling air flow rates
Solution Approach 1:
The patent introduces diffuser sections that gradually expand the cross-sectional area of cooling air passages. This geometric parameter change allows the cooling air to diffuse and spread uniformly across the component surface, significantly improving heat transfer efficiency and reducing the required cooling air flow rate while maintaining manufacturing feasibility through standard diffusion geometries
Solution Approach 2:
The patent transitions from simple linear microchannels to three-dimensional diffuser structures with varying cross-sectional areas. This dimensional evolution enables the cooling air to expand in multiple directions and uniformly cover the component surface, enhancing heat transfer without proportionally increasing structural complexity
2Loss of energy
If higher cooling air flow rates are used, then heat transfer efficiency improves, but overall turbine efficiency decreases
Solution Approach 1:
By implementing diffuser sections with optimized expansion angles and cross-sectional area variations, the patent achieves superior heat transfer efficiency at lower cooling air flow rates. This parameter optimization allows the system to maintain effective cooling while preserving more energy for turbine work output
Solution Approach 2:
The diffuser structure enables the cooling air to automatically diffuse and distribute itself uniformly across the component surface through pressure gradients and geometric constraints. This self-distribution mechanism maximizes heat transfer efficiency without requiring additional energy input or complex control systems
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 approach reduces the cooling air flow rate required while improving the heat transfer efficiency, leading to a more effective cooling system for gas turbine components.
Implementation Method 1
defining a diffuser section in at least one of the at least one delivery channel and the at least one discharge passage, such that a fluid channeled through the at least one delivery channel and the at least one discharge passage is diffused prior to discharge adjacent the defined portion of the outer surface
Implementation Method 2
an internal structure within the component is cooled using cooling air or other fluid that is channeled through microchannels defined within the internal structure
Implementation Method 3
After receiving heat from the internal structure of the component, the cooling air is exhausted from the microchannels and discharged into the trench
Data Source
AI summary
A system for providing cooling for a turbine component that includes an outer surface exposed to combustion gases is provided. A component base includes at least one fluid supply passage coupleable to a source of cooling fluid. At least one feed passage communicates with the at least one fluid supply passage. At least one delivery channel communicates with the at least one feed passage. At least one cover layer covers the at least one feed passage and the at least one delivery channel, defining at least in part the component outer surface. At least one discharge passage extends to the outer surface. A diffuser section is defined in at least one of the at least one delivery channel and the at least one discharge passage, such that a fluid channeled through the system is diffused prior to discharge adjacent the outer surface.