Gas Turbine Burner Fuel Ejection Uniformity
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Solution Overview
Problem
The combustion burner in JP 2003-74855 A experiences fuel vortices in gas fuel passage portions, leading to varying fuel ejection from small holes and increased NOx emissions in gas turbine combustors.
Innovation Solution
A gas turbine combustion burner design featuring a nozzle with radially arranged swirling vanes, including first and second fuel passages, where the second passages disperse dynamic pressure to prevent vortices, ensuring uniform fuel ejection from ejection holes, and optionally incorporating a rectifier grid or pressure loss member to enhance this effect.
Engineering Contradictions & Design Principles
Engineering Contradiction Analysis
1Device complexity
If fuel is supplied through a single fuel passage into cavities in swirling vanes, then the structure is simple, but vortices form in the cavities causing varying fuel ejection and increased NOx emissions
Solution Approach 1:
The single fuel passage is divided into multiple separate fuel passages (first fuel passage and second fuel passage). The first fuel passage supplies fuel to multiple cavities, while the second fuel passage supplies fuel to at least one cavity. This segmentation prevents vortex formation in individual cavities by providing separate, controlled fuel supply paths, thereby achieving uniform fuel ejection from all ejection holes while maintaining reasonable structural complexity.
2Manufacturing precision
If multiple fuel passages are used to supply fuel to cavities, then fuel ejection uniformity improves, but the device complexity increases
Solution Approach 1:
The first fuel passage serves multiple functions by supplying fuel to multiple cavities simultaneously. The second fuel passage complements this by supplying fuel to at least one cavity. This multi-functional design achieves uniform fuel ejection across all ejection holes while minimizing the increase in device complexity through efficient resource utilization.
3Object-affected harmful factors
If fuel passages are designed to prevent vortex formation, then NOx emissions are reduced, but the fuel passage design becomes more complex
Solution Approach 1:
By segmenting the fuel supply system into multiple passages (first and second fuel passages), each passage can be optimized to supply fuel to specific cavities without causing vortex formation. This segmentation approach reduces NOx emissions by preventing vortices while keeping each individual passage relatively simple in design.
Solution Approach 2:
Different fuel passages are designed with different characteristics suited to their specific functions. The first fuel passage is configured for supplying fuel to multiple cavities, while the second fuel passage is configured for supplying fuel to at least one cavity. This local optimization of fuel passage design prevents vortex formation in each cavity while maintaining overall system simplicity.
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 design achieves uniform fuel ejection from the combustion burner, reducing NOx emissions in gas turbine combustors by preventing vortex formation and ensuring consistent fuel distribution.
Implementation Method 1
As the fuel passes through the second fuel passages, dynamic pressure generated in the first fuel passage is dispersed so that the fuel flows (is supplied) evenly (uniformly) from the individual second fuel passages into the cavities, thus preventing the formation of vortices in the cavities.
Implementation Method 2
a plurality of swirling vanes for ejecting fuel from fuel ejection holes into air or a mixture of air and fuel flowing from an upstream side while applying a swirling force to form a swirling mixed airflow
Implementation Method 3
a slit-like second fuel passage is provided between the cavity and the first fuel passage along an axial direction, and a rectifier grid is disposed at an exit or entrance end of the second fuel passage. As the fuel passes through the second fuel passages and the rectifier grids, dynamic pressure generated in the first fuel passage is dispersed
Implementation Method 4
a pressure loss member is disposed in the first fuel passage near the upstream side of the second fuel passage. As the fuel passes through the second fuel passages and the pressure loss member, dynamic pressure generated in the first fuel passage is dispersed
Data Source
Figure 1
Figure 2
Figure 3~4
AI summary
A combustion burner for a gas turbine, configured so that fuel is uniformly ejected from ejection holes to reduce the NOx generation of the gas turbine combustor. A combustion burner for a gas turbine, provided with: rotating vanes (20) for ejecting fuel from fuel ejection holes (23, 24) to air or a mixture gas of air and fuel, which flows from the upstream side, and applying a swirling force to the air or the mixture gas to create a swirling mixture gas flow; and a nozzle (21) which have the rotating vanes (20) disposed in a radiating manner on the outer peripheral surface thereof and which have formed therein a first fuel flow path (26) for guiding the fuel to the fuel ejection holes (23, 24). The rotating vanes (20) have provided therein cavities (25) which communicate with the fuel ejection holes (23, 24), and at least two second fuel flow paths (27) are provided between each cavity (25) and the first fuel flow path (26) so as to extend in the axial direction.