Airfoil Cooling Holes Positioned by Cartesian Coordinates
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Solution Overview
Problem
Gas turbine engine components in hot sections face increased stress and wear due to high gas path temperatures and pressures, requiring effective cooling to maintain efficiency and service life.
Innovation Solution
The airfoil in gas turbine engines features a plurality of cooling holes positioned according to specific X, Y, and Z Cartesian coordinate values, directing cooling fluid to reduce surface temperatures, particularly in the midspan region, and potentially cooling downstream components.
Engineering Contradictions & Design Principles
Engineering Contradiction Analysis
1Reliability
If cooling holes are added to airfoils in hot sections, then service life and reliability are improved, but device complexity increases
Solution Approach 1:
The cooling holes are strategically positioned at specific X, Y, and Z coordinates on the airfoil surfaces, concentrating cooling resources at locations most susceptible to thermal damage. This localized approach ensures effective cooling where needed while avoiding unnecessary complexity in regions experiencing lower thermal loads.
Solution Approach 2:
The patent specifies cooling hole positions using three-dimensional Cartesian coordinates (X, Y, Z), transitioning from conventional two-dimensional surface patterns to a three-dimensional spatial distribution. This dimensional approach enables precise targeting of cooling fluid flow paths to critical thermal zones on the airfoil.
2Reliability
If cooling fluid flow is increased to reduce surface temperatures, then component reliability improves, but energy consumption increases
Solution Approach 1:
Cooling fluid is directed through specifically positioned holes at predetermined coordinates, concentrating the cooling effect at locations experiencing highest thermal stress. This localized cooling reduces the total volume of cooling fluid required compared to uniform cooling approaches, thereby reducing energy consumption while maintaining component reliability.
Solution Approach 2:
The patent utilizes the existing hot gas flow patterns and thermal gradients to inform cooling hole placement, converting the harmful effect of non-uniform heating into a beneficial cooling strategy. By positioning holes where thermal stress is highest, the system efficiently addresses the most critical thermal problems with minimal additional energy input.
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 cooling configuration effectively reduces surface temperatures and extends the service life of gas turbine engine components by managing thermal loads and maintaining efficiency.
Implementation Method 1
directing cooling fluid to reduce surface temperatures
Data Source
AI summary
An airfoil includes a leading edge, a trailing edge, a pressure side surface extending from the leading edge to the trailing edge, a suction side surface extending from the leading edge to the trailing edge and generally opposite the pressure side surface and a plurality of cooling holes. The cooling holes are positioned on the airfoil in accordance with X, Y and Z Cartesian coordinate values set forth in an accompanying Table.