Turbine Blade Cooling Hole Distribution for Heat Dissipation
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Solution Overview
Problem
High-pressure turbine blades in gas turbine engines face challenges in efficiently managing heat loading and mechanical stress due to elevated temperatures and pressures, requiring effective cooling solutions that are not adequately addressed by current designs.
Innovation Solution
The design incorporates a turbine blade with a specific airfoil shape and cooling hole distribution, featuring multiple sets of cooling holes with precise Cartesian coordinate locations to enhance fluid communication and heat dissipation, including sets A1 to F6, which are strategically positioned to optimize cooling fluid flow and distribution within the blade.
Engineering Contradictions & Design Principles
Engineering Contradiction Analysis
1Temperature
If cooling holes are added to the turbine blade to improve cooling efficiency, then heat dissipation is enhanced, but the structural strength and integrity of the blade may be compromised
Solution Approach 1:
The patent applies local quality by varying the cooling hole distribution, size, and orientation in different regions of the blade airfoil. Each set of cooling holes (A1-A8, B1-B10, C1-C9, D1-D6, E1-E7, F1-F6) is strategically positioned and dimensioned to address specific thermal zones, providing enhanced cooling where heat loading is highest while preserving structural integrity in load-critical areas.
Solution Approach 2:
The cooling system is segmented into multiple distinct sets of cooling holes rather than a single uniform pattern. This segmentation allows independent optimization of each hole set for its specific location and thermal requirement, enabling the blade to achieve effective cooling across the entire airfoil while maintaining structural strength through careful placement and dimensioning of each segment.
2Reliability
If multiple sets of cooling holes are implemented with precise coordinate locations, then cooling fluid distribution is optimized, but manufacturing complexity increases
Solution Approach 1:
The patent employs parameter changes by defining six distinct sets of cooling holes with varying parameters including hole diameter, orientation angles, depth, and spatial coordinates. Each set is tailored to its specific location on the blade airfoil, with parameters optimized to achieve uniform cooling fluid distribution across different thermal zones while maintaining manufacturability through systematic parameter variation rather than arbitrary complexity.
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 effectively enhances the cooling efficiency of high-pressure turbine blades, improving their thermal and mechanical performance by ensuring adequate heat dissipation and reducing the risk of damage from high temperatures and pressures.
Implementation Method 1
the perimeter wall having a plurality of cooling holes defined therethrough and providing fluid communication between the at least one enclosure and a gaspath of the gas turbine engine
Implementation Method 2
This configuration effectively enhances the cooling efficiency of high-pressure turbine blades, improving their thermal and mechanical performance by ensuring adequate heat dissipation
Data Source
AI summary
A turbine blade for a gas turbine engine with an airfoil portion defined by a perimeter wall surrounding at least one enclosure, the perimeter wall having a plurality of cooling holes defined therethrough and providing fluid communication between the at least one enclosure and a gaspath of the gas turbine engine. The plurality of cooling holes includes at least one set of holes selected from the group consisting of a first set, a second set, a third set, a fourth set, a fifth set and a sixth set, wherein the first, second, third, fourth, fifth and sixth sets of holes respectively include the holes numbered A1 to A8, B1 to B10, C1 to C9, D1 to D6, E1 to E7 and F1 to F6 each located such that a central axis thereof extends through the respective point 1 and point 2 having a nominal location in accordance with the X, Y, Z Cartesian coordinate values set forth in Table 3.