Vortex Generators for Turbine Airfoil Heat Transfer
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Solution Overview
Problem
Existing gas turbine airfoils face challenges in enhancing heat transfer within internal cavities, particularly in confined and hard-to-access areas, where traditional methods like pin-fin banks and turbulators are less effective.
Innovation Solution
The use of vortex generators on internal surfaces of airfoils, specifically delta wing, rib winglet, and wedge-shaped designs, to shed vortices and enhance heat transfer by reducing boundary layer height and promoting fluid exchange within internal cooling cavities.
Engineering Contradictions & Design Principles
Engineering Contradiction Analysis
1Temperature
If traditional pin-fin banks and turbulators are used to enhance heat transfer, then heat transfer is improved, but they are less effective in confined internal cavities and hard-to-access areas
Solution Approach 1:
The patent applies vortex generators specifically in confined internal cavities and hard-to-access areas of turbine airfoils, tailoring the heat transfer enhancement solution to the specific geometric constraints of these regions rather than using uniform traditional methods throughout
Solution Approach 2:
The patent introduces vortex generators that create three-dimensional vortical flow structures within the two-dimensional boundary layer, adding a vertical dimension to the flow dynamics and enabling effective heat transfer enhancement in confined spaces where traditional pin-fin banks cannot be accommodated
2Temperature
If compressed air is used for cooling purposes, then component temperatures are maintained within requirements, but engine performance and efficiency are reduced
Solution Approach 1:
The patent changes the flow regime parameters within the cooling cavities by introducing vortex generators, transforming the flow from laminar to turbulent and increasing the convective heat transfer coefficient, thereby improving cooling efficiency and reducing the amount of coolant air required
3Stability of the object's composition
If boundary layer develops and grows along internal surfaces, then flow stability is maintained, but heat transfer is reduced
Solution Approach 1:
The vortex generators create periodic vortical structures that mechanically disrupt the boundary layer, causing oscillations and mixing that prevent the boundary layer from becoming too thick and stable, thereby maintaining heat transfer efficiency
Solution Approach 2:
The patent converts the harmful effect of boundary layer growth (which reduces heat transfer) into a beneficial phenomenon by using the boundary layer itself as the medium through which vortices are generated and propagated, creating controlled disruptions that enhance heat transfer
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
Vortex generators significantly improve heat transfer within airfoil cavities by reducing boundary layer height and increasing heat transfer efficiency compared to traditional methods, while being suitable for manufacturing in hard-to-reach areas.
Implementation Method 1
a plurality of vortex generators formed on an internal surface of at least one of the pressure and suction sides of the airfoil, the plurality of vortex generators arranged in radially spaced relationship in the one of the plurality of internal cooling cavities
Implementation Method 2
heat transfer is reduced as the height of a boundary layer develops and grows. Pin-fin banks and turbulators create a disruption in the boundary layer that allows the boundary layer to restart
Implementation Method 3
Traditionally, temperatures of gas turbine components have been maintained within requirements by convection cooling and thermal barrier coatings
Data Source
AI summary
An airfoil includes a leading edge, a trailing edge, a suction side and a pressure side; a plurality of internal cooling cavities extending radially within the airfoil, one of the plurality of internal cavities extending along the trailing edge. The trailing edge is provided with a plurality of coolant exit apertures extending therealong. A plurality of vortex generators is formed on an internal surface of at least one of the pressure and suction sides of the airfoil. The vortex generators are arranged in radially spaced relationship in one of the plurality of internal cooling cavities, extending substantially parallel to and in proximity to the plurality of coolant exit apertures.