Gas Turbine Burner Vortex Generator Lobed Trailing Edge
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Solution Overview
Problem
Existing gas turbine burners face challenges in achieving homogeneous fuel-air mixing due to space limitations, and manufacturing complex vortex generators with multiple lobed shapes is costly and complex.
Innovation Solution
The burner design incorporates vortex generators with a trailing edge featuring a first order lobed shape defined by a second order lobed shape, with additional lobed-shaped walls near the nozzles to enhance mixing, reducing manufacturing complexity and cost by limiting higher order lobed shapes to areas around the nozzles.
Engineering Contradictions & Design Principles
Engineering Contradiction Analysis
1Manufacturing precision
If vortex generators with multiple lobed shapes (first order and second order) are used throughout the entire structure, then mixing performance is improved, but manufacturing complexity and cost increase
Solution Approach 1:
The patent applies local quality by providing second order lobed shape only in specific zones around the nozzles where fuel injection occurs, rather than throughout the entire vortex generator structure. This localized approach concentrates the mixing enhancement where it is most needed while reducing overall manufacturing complexity and cost.
Solution Approach 2:
The vortex generator structure is segmented into different zones with different levels of complexity: a first order lobed shape throughout the structure for baseline turbulence, and second order lobed shape only in specific zones around nozzles for enhanced mixing. This segmentation allows optimization of performance versus manufacturing complexity.
2Productivity
If vortex generators with complex lobed shapes are used, then fuel-air mixing efficiency is improved, but manufacturing cost increases
Solution Approach 1:
Complex second order lobed shape is applied only in local zones around the nozzles where fuel-air mixing is most critical, rather than throughout the entire vortex generator. This reduces manufacturing cost while maintaining high mixing efficiency where it matters most.
Solution Approach 2:
Instead of applying complex lobed shapes throughout the entire structure (excessive action), the patent applies them only partially in zones around the nozzles. This partial action is sufficient to achieve the required mixing efficiency while reducing manufacturing cost.
3Volume of moving object
If space limitations in the burner are considered, then compact design is achieved, but homogeneous mixing of fuel and air becomes more difficult
Solution Approach 1:
The patent uses lobed shapes (curved geometries) in the vortex generators to generate rotational flow and turbulence. These curved structures enhance mixing through vortex formation and fluid rotation, achieving homogeneous mixing in a compact space without requiring large burner dimensions.
Solution Approach 2:
The lobed shapes in the vortex generators create oscillating flow patterns and turbulence as fluid passes through them. This mechanical disturbance enhances mixing efficiency, allowing homogeneous fuel-air mixing to be achieved in the limited space available in the burner.
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 configuration achieves efficient fuel-air mixing by generating high turbulence around the nozzles while minimizing unnecessary complexity and cost, ensuring effective combustion in gas turbines.
Implementation Method 1
the burners have a duct which includes structures creating turbulence. The air/hot gas passes through these structures acquiring turbulence; the fuel is injected in the turbulent flow such that quick mixing is achieved
Data Source
Figure 1~2
Figure 3~6
Figure 7~10
AI summary
The burner (1) of a gas turbine has a duct (2), a vortex generator (3) extending in the duct (2) and comprising a leading edge (4) and a trailing edge (5). The trailing edge (5) has a first order lobed shape (6). The first order lobed shape (6) is defined by a second order lobed shape (7). Preferably a nozzle (8) for fuel injection is connected to the vortex generator (3) and the second order lobed shape (7) is only provided at the nozzles (8).