Turbine Blade Cooling Holes Suction Side Film Cooling
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Solution Overview
Problem
Gas turbine engine turbine blades face extreme temperatures, necessitating effective cooling to enhance durability and performance, but existing cooling methods may not adequately address the high thermal stresses.
Innovation Solution
The design incorporates a turbine blade with a plurality of cooling holes on the suction side of the airfoil, strategically located and in fluid communication with an internal cavity, with specific hole diameters and coordinates defined in Tables 1 and 2, allowing for efficient film cooling.
Engineering Contradictions & Design Principles
Engineering Contradiction Analysis
1Temperature
If cooling holes are added to turbine blade, then cooling efficacy is improved, but blade structure complexity increases
Solution Approach 1:
The turbine blade is segmented into multiple functional zones with different cooling hole patterns. The suction side contains a first plurality of cooling holes while the pressure side contains a second plurality of cooling holes, allowing independent optimization of cooling in each zone. This segmentation enables targeted cooling where needed without uniformly complicating the entire blade structure.
Solution Approach 2:
Different regions of the turbine blade are provided with different cooling characteristics. The suction side cooling holes have specific diameter ranges (0.010-0.020 inches) and coordinates optimized for suction side thermal conditions, while pressure side holes are configured differently. This local quality approach ensures each area receives appropriate cooling without unnecessary structural complexity elsewhere.
2Temperature
If cooling air flow is increased, then thermal management is improved, but energy loss increases
Solution Approach 1:
The cooling hole parameters are precisely controlled to optimize cooling efficiency while minimizing energy loss. Hole diameters are specified within narrow ranges (0.010-0.020 inches for suction side holes) and coordinates are precisely defined in Tables 1 and 2. These parameter changes ensure efficient cooling air utilization without excessive energy consumption.
Solution Approach 2:
The cooling system utilizes controlled air flow through precisely engineered hole configurations. The suction side cooling holes are positioned and sized to create effective film cooling that adheres to the blade surface, maximizing cooling efficiency. The air flow is directed through internal cavities and out through strategically located holes to achieve optimal thermal management with minimal energy penalty.
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 provides enhanced cooling efficacy by directing cooling air to critical areas, improving the blade's thermal management and performance under high-temperature conditions.
Implementation Method 1
a plurality of cooling holes defined therein, at least some of the plurality of cooling holes being located on a suction side of an airfoil of the turbine blade and in fluid communication with an internal cavity of the turbine blade
Data Source
AI summary
A turbine blade for a gas turbine engine. The turbine blade having a plurality of cooling holes defined therein, at least some of the plurality of cooling holes being located on a suction side of an airfoil of the turbine blade and in fluid communication with an internal cavity of the turbine blade; and wherein the at least some of the plurality of cooling holes are located in the airfoil according to the coordinates of Tables 1 and/or 2.