Turbine Airfoil Insert for Heat Transfer
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Solution Overview
Problem
Turbine engines face challenges in achieving effective cooling of high-temperature components while maintaining efficiency, as conventional cooling methods are inadequate for the heightened operational and environmental demands.
Innovation Solution
An airfoil design for turbine engines incorporates an insert with a non-constant cross-sectional area within the cooling passage, creating a varying gap between the insert and the passage's inner surface, which increases the heat transfer coefficient by enhancing airflow velocity and local heat transfer.
Engineering Contradictions & Design Principles
Engineering Contradiction Analysis
1Temperature
If conventional cooling passages are used in turbine airfoils, then the structure is simple and easy to manufacture, but the heat transfer coefficient is insufficient for high-temperature operation
Solution Approach 1:
The insert introduces local geometric variations within the cooling passage, creating regions of different gap sizes (smaller near the leading edge, larger toward the trailing edge) to optimize heat transfer coefficients at different locations along the airfoil surface, addressing the insufficient heat transfer in high-temperature turbine operation
Solution Approach 2:
The insert modifies the flow passage geometry by creating a variable gap between the insert surface and the cooling passage wall, changing the hydraulic diameter and flow velocity distribution to enhance convective heat transfer coefficients without requiring a complete redesign of the cooling passage system
2Temperature
If cooling air is ducted from compressors to turbine components, then cooling is achieved, but engine efficiency is reduced due to temperature differences
Solution Approach 1:
The insert utilizes the existing cooling air flow from the compressor through the cooling passage, enhancing its cooling effectiveness by modifying the flow geometry rather than requiring additional cooling resources, thereby maintaining engine efficiency while improving cooling performance
3Use of energy by moving object
If turbine blades operate at high temperatures to maximize efficiency, then engine efficiency is improved, but cooling requirements increase
Solution Approach 1:
The insert creates location-specific flow characteristics within the cooling passage, with varying gap sizes that optimize heat transfer at different positions (smaller gaps near leading edge for high heat flux, larger gaps toward trailing edge), enabling effective cooling that supports high-temperature operation for maximum engine efficiency
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 increasing the heat transfer coefficient along the airfoil's outer wall, allowing for more effective heat management and tailored cooling based on the airfoil's specific needs, while maintaining minimal weight and ease of maintenance.
Implementation Method 1
The gap is non-constant along the sidewall and increases extending along the flow direction... increasing the heat transfer coefficient by enhancing airflow velocity
Implementation Method 2
cooling is accomplished by ducting cooler air from the high and/or low pressure compressors to the engine components that require cooling
Implementation Method 3
increasing the heat transfer coefficient along the airfoil's outer wall, allowing for more effective heat management
Data Source
AI summary
An apparatus and method for improving the heat transfer coefficient for an engine component for a turbine engine such as an airfoil. The airfoil can include an outer wall defining an interior. A cooling passage can be formed in the interior defining a flow direction. An insert can be provided in the cooling passage to occupy a volume of the cooling passage to maintain a threshold Mach number for an airflow passing through the cooling passage to improve the heat transfer coefficient.