Airfoil Cooling Circuit Segmentation for Thermal Uniformity
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Solution Overview
Problem
Turbine engines face challenges in efficiently cooling high-temperature components like the high pressure turbine, where existing cooling methods may not adequately manage thermal gradients and reduce fuel consumption.
Innovation Solution
The implementation of a dual cooling system comprising skin cooling circuits and wall cooling passages, each with separate internal supply circuits, to effectively distribute cooling airflow both within the airfoil's interior and on its outer surface, enhancing thermal management and structural integrity.
Engineering Contradictions & Design Principles
Engineering Contradiction Analysis
1Temperature
If traditional interior cooling circuits are used to cool turbine blades, then cooling coverage is provided, but cooling airflow requirements are high and thermal gradients are not adequately managed
Solution Approach 1:
The cooling system is segmented into two independent circuits: wall cooling passages located within the airfoil wall and skin cooling circuits formed on the outer surface. This segmentation allows each circuit to be optimized for its specific function, with wall cooling providing structural cooling and skin cooling providing surface temperature control, thereby reducing total cooling airflow requirements while improving thermal uniformity
Solution Approach 2:
The invention transitions from traditional three-dimensional interior cooling passages to a two-dimensional skin cooling circuit on the outer surface. This dimensional change allows cooling airflow to be distributed across the surface area rather than through volumetric passages, improving heat transfer efficiency and reducing the quantity of cooling air needed while better managing thermal gradients across the airfoil surface
2Temperature
If dedicated cooling circuits are provided for different portions of the blade, then localized cooling is achieved, but device complexity increases
Solution Approach 1:
The invention merges the functions of multiple dedicated cooling circuits into an integrated dual-circuit system where wall cooling passages and skin cooling circuits work together. The first and second supply circuits can be selectively activated based on operational requirements, providing localized cooling capability without the complexity of multiple independent dedicated circuits for each blade portion
3Temperature
If cooling air is ducted from compressors to turbine components, then cooling is achieved, but fuel consumption increases
Solution Approach 1:
The invention changes the parameters of cooling air utilization by implementing a dual-circuit system that optimizes airflow distribution between wall and skin cooling. This allows more effective use of cooling air, reducing the total quantity required from compressor bleed and thereby reducing the energy penalty and fuel consumption associated with cooling turbine components
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 dual cooling system reduces cooling airflow requirements by 30-50% compared to traditional methods, decreases specific fuel consumption, and improves thermal uniformity, ensuring continued engine operation even if one cooling system fails.
Implementation Method 1
passing a cooling airflow from a source in parallel to an interior of an outer wall of an airfoil to form a wall cooling circuit, and to a channel in an outer surface of the outer wall, and then to a hole in a coating overlying the outer surface to form a skin cooling circuit
Data Source
AI summary
An airfoil for a turbine engine having an engine component including an internal cooling circuit fluidly coupled to a plurality of passages within the outer wall of the engine component where cooling air moves from the internal cooling circuit to an outer surface of the engine component through the passages.