Turbine Blade Tip Cooling Hole Layout for Uniform Airflow
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Solution Overview
Problem
Turbine blade tips face challenges in effectively cooling high-temperature gas turbines due to limitations in existing cooling structures and methods.
Innovation Solution
The design incorporates a blade tip with a circumferential wall featuring evenly spaced cooling air holes and supply air channels that distribute cooling air from the interior of the turbine blade, enhancing cooling efficiency through strategic placement and distribution.
Engineering Contradictions & Design Principles
Engineering Contradiction Analysis
1Temperature
If cooling air holes are added to the blade tip, then cooling efficiency is improved, but manufacturing complexity increases
Solution Approach 1:
The blade tip is segmented into multiple functional zones with different hole patterns. The circumferential wall contains cooling air holes arranged in specific patterns, while the blade body has separate cooling structures. This segmentation allows optimized cooling in each zone without requiring complete redesign of the entire blade structure.
Solution Approach 2:
Different regions of the blade tip are provided with different cooling characteristics. The circumferential wall has cooling air holes for peripheral cooling, while the blade body has internal cooling channels. This local differentiation ensures that each area receives appropriate cooling based on its thermal load, improving overall cooling efficiency without uniform complexity throughout.
2Temperature
If cooling air holes are drilled in the circumferential wall, then heat dissipation is improved, but structural strength may be reduced
Solution Approach 1:
The cooling air holes are strategically positioned in the circumferential wall where they provide maximum cooling benefit with minimum impact on structural integrity. The hole distribution pattern optimizes heat dissipation in the thin-walled circumferential region without compromising the load-bearing capacity of the blade tip.
Solution Approach 2:
The blade tip is constructed as a composite structure combining the circumferential wall with the blade body. This composite design allows the circumferential wall to be optimized for cooling with multiple air holes, while the overall structural strength is maintained through the integrated blade body structure.
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 design improves cooling efficiency by ensuring consistent airflow distribution, reducing thermal stress, and potentially extending the lifespan of turbine blades.
Implementation Method 1
cooling air flows out from the interior of the turbine blade through supply air channels (32) and cooling air holes (25)
Data Source
AI summary
A turbine blade tip, turbine blade and method where improved cooling is made possible by an improved cooling structure with cooling air holes inside a depression in a blade tip and a special arrangement of multiple cooling air holes which are supplied by a single cooling air channel inside a wall.