Airfoil Platform Cooling Channels for Heat Transfer
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Solution Overview
Problem
Gas turbine engine airfoil platforms face challenges in efficiently managing high temperatures and pressures, leading to inadequate heat transfer coefficients and potential thermal cycling issues, despite existing cooling systems.
Innovation Solution
A cooling system is designed for airfoil platforms with multiple channels extending through the platforms, directing cooling airflow from one circumferential side to the opposite side, with outlets on the mating surfaces, enhancing heat transfer while maintaining a limited pressure drop.
Engineering Contradictions & Design Principles
Engineering Contradiction Analysis
1Temperature
If cooling air is extracted from the compressor section to cool turbine components, then the temperature of cooled components is reduced, but the pressure drop in the cooling system increases
Solution Approach 1:
The cooling system is divided into multiple independent channels (first channel, second channel, third channel) with distinct functions. The first channel provides internal platform cooling, the second channel delivers cooling air to adjacent platforms, and the third channel provides film cooling at the trailing edge. This segmentation allows optimized cooling for each zone without requiring high pressure drop across the entire system.
Solution Approach 2:
Different cooling strategies are applied to different regions of the platform based on local thermal requirements. The first channel targets the platform's internal structure, the second channel addresses mating surfaces of adjacent platforms, and the third channel protects the trailing edge. This local quality approach ensures efficient heat transfer where needed while minimizing overall pressure drop.
2Reliability
If cooling channels are extended through the platform to improve heat transfer, then the heat transfer coefficient increases, but the pressure drop across the platform increases
Solution Approach 1:
The cooling function is segmented into three separate channels rather than using one long channel extending through the entire platform. Each channel is optimized for its specific function and location, reducing the overall pressure drop while maintaining effective heat transfer in critical areas.
Solution Approach 2:
The second channel extracts cooling air from the first channel's flow path to deliver to adjacent platforms, and the third channel extracts from the second channel for trailing edge film cooling. This extraction approach allows multiple cooling functions to be achieved without requiring a single high-pressure-drop channel through the entire platform.
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
The cooling system effectively increases heat transfer coefficients in areas exposed to hot gas path air, providing improved thermal management with reduced pressure drop, thereby enhancing the durability and performance of airfoil platforms.
Implementation Method 1
The first channel may be configured to direct a cooling airflow from a first circumferential side of the airfoil, internally through the platform, and to the second mating surface of the platform
Implementation Method 2
A cooling system is designed for airfoil platforms with multiple channels extending through the platforms, directing cooling airflow from one circumferential side to the opposite side
Data Source
AI summary
An airfoil may include an airfoil body, a root and a platform disposed between the airfoil body and the root. The platform may have a first mating surface and a second mating surface. The platform may include a pocket defined by an inner diameter surface of the platform proximate the first mating surface. A channel may be defined in the platform with an outlet of the channel defined in the second mating surface.