Gas Turbine Cooling Module with Interconnected Flow Sections
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Solution Overview
Problem
Existing cooling methods for gas turbine components, such as conduits and airfoils, face inefficiencies in heat transfer and film cooling, leading to non-uniform wall temperatures and thermal degradation due to poor heat transfer characteristics and gaps between apertures, which are inadequately cooled.
Innovation Solution
The implementation of a cooling module with interconnected flow sections and chambers that facilitate a radial, longitudinal, and circumferential flow of cooling fluid within the components, ensuring uniform cooling by connecting input and output ports across multiple sections to enhance heat transfer and reduce thermal stress.
Engineering Contradictions & Design Principles
Engineering Contradiction Analysis
1Temperature
If cooling air is supplied along the outer surface of the conduit to provide direct convection cooling, then cooling effectiveness is improved, but the cooling air consumption increases
Solution Approach 1:
The patent applies local quality by providing cooling apertures at specific critical locations (leading edge, trailing edge, and intermediate positions) rather than uniform cooling across the entire surface. The cooling air is directed to specific high-heat zones through the aperture array, optimizing cooling effectiveness while reducing overall air consumption compared to full-surface cooling.
Solution Approach 2:
The patent utilizes pneumatic principles by injecting cooling air through apertures into the hot gas flow path. The cooling air is introduced in a controlled manner to create a cooling film and induce convective cooling, leveraging fluid dynamics to achieve efficient heat transfer with optimized air usage.
2Stability of the object's composition
If film cooling is established along the wall surface, then cooling uniformity is improved, but the turbulent environment of gas turbine makes it difficult to maintain
Solution Approach 1:
The patent applies preliminary action by pre-cooling the air before it reaches the critical wall surfaces through the aperture array. The cooling air is introduced in advance into the hot gas stream, allowing it to establish a protective cooling film before the hot gases can cause thermal degradation. This proactive cooling approach maintains film stability despite turbulent conditions.
Solution Approach 2:
The patent utilizes parameter changes by varying the cooling air temperature, pressure, and flow rate to optimize film cooling performance. The cooling air parameters are adjusted to match the local thermal conditions and maintain a stable cooling film under turbulent gas turbine operating conditions.
3Temperature
If cooling apertures are provided to deliver cool air to critical regions, then cooling effectiveness is improved, but gaps between apertures are exposed to less cooling air and more susceptible to thermal degradation
Solution Approach 1:
The patent applies continuity of useful action by creating an overlapping pattern of cooling air jets from adjacent apertures. The cooling air flow from each aperture extends to cover the gap regions, ensuring continuous cooling coverage across the entire surface. This continuous cooling action prevents thermal degradation at aperture gaps while maintaining effectiveness at critical regions.
4Power
If more cooling air is supplied to operate machinery at higher power levels, then power output is improved, but cooling air consumption increases
Solution Approach 1:
The patent applies local quality by concentrating cooling air supply at critical high-heat regions (leading edge, trailing edge, and intermediate zones) rather than distributing it uniformly. This targeted approach provides sufficient cooling to enable higher power operation while minimizing overall cooling air consumption compared to full-surface cooling.
Solution Approach 2:
The patent applies partial action by providing cooling only where absolutely necessary to maintain component integrity at high power levels. The aperture array is strategically positioned to cover critical thermal zones, using cooling air partially rather than fully, thereby enabling high power output with reduced air consumption.
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 configuration improves cooling effectiveness by maintaining a uniform cooling film along the surfaces, reducing thermal degradation, and enhancing the ability to operate gas turbines at higher power levels with more efficient heat management.
Implementation Method 1
improves cooling effectiveness by maintaining a uniform cooling film along the surfaces, reducing thermal degradation
Implementation Method 2
facilitate a radial, longitudinal, and circumferential flow of cooling fluid within the components, ensuring uniform cooling
Data Source
AI summary
A cooling arrangement in a gas turbine system (120). The arrangement includes a plurality of flow network units (208) to transfer heat to cooling fluid, at least one unit including first (218), second (220), and third (222) flow sections between openings (64a) in a first wall (66) and an opening in a second wall (68) to pass cooling fluid through the walls. The first section includes first flow paths, between the openings in the first wall and the second section, extending to the second section. The third section includes third flow paths, between the second section and the opening in the second wall, to effect flow of cooling fluid. The second section includes one or more cooling fluid flow paths between the first section and the third section. The number of flow paths in the second section is fewer than the number of first flow paths and fewer than the number of third flow paths.