Gas Turbine Blade Impingement Cooling via Crossover Holes
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Solution Overview
Problem
Existing gas turbine engine cooling methods, such as serpentine paths and micro-circuits, are inefficient in cooling the sides of airfoils and require complex manufacturing, while impingement cooling has not been used extensively due to manufacturing simplicity but limited application.
Innovation Solution
The implementation of central cooling channels with crossover holes that supply impingement cooling air to both suction and pressure walls, combined with film cooling holes for outer surface cooling, providing efficient and straightforward manufacturing of cooling paths.
Engineering Contradictions & Design Principles
Engineering Contradiction Analysis
1Reliability
If serpentine paths or micro-circuits are used for cooling, then cooling coverage is improved, but manufacturing complexity increases
Solution Approach 1:
The cooling system is segmented into multiple independent impingement cooling channels, each supplied by separate feed channels. This segmentation allows each channel to be manufactured independently using simple drilling operations, avoiding the complex serpentine paths while maintaining comprehensive cooling coverage through distributed channel placement
Solution Approach 2:
The invention transitions from two-dimensional serpentine surface paths to three-dimensional impingement cooling channels that penetrate through the airfoil thickness. By directing cooling air perpendicular to the airfoil surfaces from internal channels, the system achieves effective cooling with simpler linear channel geometries rather than complex surface-wrapping paths
2Ease of manufacture
If radial cooling paths are used, then manufacturing is simplified, but cooling efficiency near the tip deteriorates
Solution Approach 1:
The cooling channel configuration is optimized locally for different regions of the airfoil. Feed channels and impingement channels are strategically positioned and sized to deliver adequate cooling flow to both root and tip regions, with channel densities and dimensions adjusted to match local thermal requirements rather than using uniform radial paths
3Ease of manufacture
If impingement cooling channels are placed only at leading or trailing edges, then manufacturing is simplified, but cooling coverage of airfoil sides is insufficient
Solution Approach 1:
The cooling system is divided into multiple discrete impingement cooling channels distributed across the airfoil structure. These segmented channels are positioned to target specific high-heat-flux regions including leading edges, trailing edges, and critically, the suction and pressure sides, providing comprehensive surface coverage while maintaining simple channel geometries
Solution Approach 2:
The impingement cooling channel design serves multiple functions simultaneously: it cools leading edges, trailing edges, and airfoil sides through strategically positioned outlets; it provides structural support; and it enables simple manufacturing through direct drilling. This multi-functional design eliminates the need for separate cooling systems for different airfoil regions
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 solution achieves efficient cooling of the entire airfoil surface through impingement cooling, simplifying the manufacturing process and ensuring effective heat management across the turbine blade or vane.
Implementation Method 1
cooling air is received from a core and directed against an outer wall of the blade. Impingement cooling channels have generally not been used along the sides of the airfoils.
Implementation Method 2
film cooling holes are formed in an outer skin of the wall. The air passes through these film cooling holes to further cool an outer surface of the pressure and suction walls.
Data Source
Figure 1
Figure 2
Figure 3~4
AI summary
Turbine components, and in particular turbine blades (24), are provided with impingement cooling channels (214, 216). Air is delivered along central channels (206, 208, 210), and the central channels (206, 208, 210) deliver the air through crossover holes (212) to core channels (214, 216) adjacent both a pressure wall (85) and a suction wall (87). The air passing through the crossover holes (212) impacts against a wall of the core channels (214, 216).