Vortex Generator Trailing Edge Undulation for Gas Turbine Mixing
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Solution Overview
Problem
Existing vortex generating devices for gas turbine engines require complex geometries, leading to high manufacturing complexity, increased cost, and pressure losses, which hinder efficient fuel mixing and engine performance in sequential combustion systems.
Innovation Solution
A vortex generating device with a streamlined, airfoil-shaped body featuring a non-undulating leading edge and a trailing edge with specific convex and concave sections that reduce pressure loss while maintaining vortex strength for efficient fuel mixing, utilizing a trailing edge design that undulates over at most half a wavelength to minimize pressure loss and maximize mixing efficiency.
Engineering Contradictions & Design Principles
Engineering Contradiction Analysis
1Manufacturing precision
If a multiply convoluted trailing edge geometry is used to generate vortices for fuel mixing, then fuel mixing efficiency is improved, but device complexity and manufacturing difficulty increase
Solution Approach 1:
The patent applies curvature to the trailing edge by introducing a single undulation with defined convex and concave sections instead of multiple convolutions. This curved geometry generates the necessary vortices for fuel mixing while maintaining manufacturing feasibility through simplified tooling requirements
Solution Approach 2:
The trailing edge is segmented into distinct functional zones: a convex section, a concave section, and a return section. This segmentation allows each zone to contribute specifically to vortex generation while keeping the overall geometry simple enough for manufacturing
2Manufacturing precision
If a multiply convoluted trailing edge geometry is used to generate vortices, then fuel mixing capability is enhanced, but manufacturing cost increases
Solution Approach 1:
The patent adopts a trailing edge design that can be manufactured using conventional, cost-effective methods rather than requiring expensive specialized tooling. The simplified geometry allows for standard manufacturing processes, reducing both initial tooling costs and per-unit manufacturing expenses
3Speed
If vortex generating geometry is used to mix fuel and oxidant, then mixing speed is improved, but total pressure loss increases
Solution Approach 1:
The patent implements a trailing edge undulation that extends for at most half a wavelength, which is sufficient to generate the required vortices for effective mixing without creating excessive pressure losses. This partial undulation achieves the necessary mixing action while minimizing energy penalties
Solution Approach 2:
The vortex generation is localized to specific convex and concave sections of the trailing edge rather than extending along the entire trailing edge length. This localized approach creates effective vortices for mixing while reducing the overall pressure loss compared to extended undulations
4Manufacturing precision
If the undulation amplitude of the trailing edge is increased to enhance vortex strength, then fuel mixing efficiency is improved, but pressure loss increases excessively
Solution Approach 1:
The patent specifies that the trailing edge undulation extends for at most half a wavelength, providing sufficient vortex generation for effective mixing while preventing excessive pressure losses that would occur with larger or extended undulations
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 solution significantly reduces pressure loss and manufacturing complexity, enhancing fuel mixing efficiency and reducing costs, while allowing for increased undulation amplitude without excessive pressure loss, thereby improving overall engine performance.
Implementation Method 1
At least two of the camber lines, that is, the camber lines of at least two profile cross sections, exhibit different camber angles, such that the body exhibits at least two different flow deflection angles along the spanwise extent
Implementation Method 2
The body, in profile cross sections taken across the spanwise direction, exhibits an airfoil-shaped geometry, wherein each airfoil-shaped profile cross section has a camber line extending from the leading edge to the trailing edge
Implementation Method 3
The trailing edge extends from a first spanwise end to a second spanwise end, and the trailing edge, when seen from a downstream viewpoint, comprises a first section in which it is convexly shaped on the side of the first surface and is concavely shaped on the side of the second surface
Data Source
AI summary
Disclosed is a vortex generating device having a body, extending between a leading edge and a trailing edge. The body, in profile cross sections taken across the spanwise direction, exhibits an airfoil-shaped geometry. Each airfoil-shaped profile cross section has a camber line extending from the leading edge to the trailing edge, at least two of the camber lines exhibiting different camber angles, such that the body exhibits at least two different flow deflection angles along the spanwise extent. An imaginary trailing edge diagonal extends straight from a first spanwise end of the trailing edge to a second spanwise end of the trailing edge. When seen from the downstream viewpoint, the trailing edge crosses the imaginary trailing edge diagonal exactly once at one diagonal crossing point.