Gas Turbine Fuel Nozzle Assembly for Hydrogen Flashback Control
Find Innovative SolutionsGenerate Solutions
Solution Overview
Problem
Turbine engines using hydrocarbon fuels produce environmentally unwanted byproducts such as NOx, CO, UHC, and sulfur oxides, while hydrogen fuels pose challenges like flashback and flameholding due to rapid dispersion and mixing issues.
Innovation Solution
The use of fuel nozzle assemblies with outer and inner fluid passages providing swirling flows, rich and lean fuel-air mixtures, and counter-swirl configurations to enhance mixing and stability, along with air passages to control flame and reduce NOx emissions, is employed.
Engineering Contradictions & Design Principles
Engineering Contradiction Analysis
1Object-generated harmful factors
If hydrogen fuel is used, then environmentally unwanted byproducts are reduced, but flashback and flameholding occur due to rapid dispersion
Solution Approach 1:
The fuel nozzle assembly is divided into multiple nozzles (first nozzle and second nozzle) that are spatially separated. Each nozzle independently dispenses fuel into the combustion chamber, which segments the rapid dispersion problem and allows better control over flame propagation and mixing characteristics.
Solution Approach 2:
The patent applies different configurations to different nozzles: the first nozzle has a larger diameter for broader dispersion while the second nozzle has a smaller diameter for more focused flow. This local differentiation optimizes both mixing and flame stability control at different locations within the combustion chamber.
2Object-generated harmful factors
If hydrogen fuel is used, then NOx emissions are reduced, but mixing and stability issues arise
Solution Approach 1:
By dividing the fuel delivery system into multiple nozzles with different diameters, the patent creates multiple distinct mixing zones in the combustion chamber. This segmentation allows different regions to handle different mixing requirements, improving overall mixing efficiency while maintaining stability.
Solution Approach 2:
The patent introduces spatial distribution across multiple nozzles positioned at different locations and orientations in the combustion chamber. This multi-dimensional arrangement creates varied flow paths and mixing patterns, enhancing both mixing efficiency and flame stability simultaneously.
3Stability of the object's composition
If fuel nozzle assembly with multiple passages is used, then mixing is enhanced, but device complexity increases
Solution Approach 1:
Each nozzle in the assembly serves multiple functions: it dispenses fuel, creates a specific flow pattern, establishes a mixing zone, and supports flame stability. This multi-functionality reduces the need for separate components, thereby limiting the increase in overall device complexity despite having multiple nozzles.
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 lower NOx emissions, reduced flashback and flameholding, and improved flame stability, enabling the use of hydrogen fuel without diluents, applicable to various engines including turbojet, turboprop, and turbofan engines.
Implementation Method 1
fuel nozzle assemblies with outer and inner fluid passages providing swirling flows
Implementation Method 2
counter-swirl configurations to enhance mixing and stability
Implementation Method 3
air passages to control flame and reduce NOx emissions
Data Source
AI summary
A gas turbine engine, comprising a compressor section, combustion section, and turbine section in serial flow arrangement, with the combustion section comprising: a combustor liner that at least partially defines a combustion chamber; and a gaseous fuel nozzle assembly, comprising: a rich fuel supply configured to provide a rich mixture of gaseous fuel and air; a lean fuel supply configured to provide a lean mixture of gaseous fuel and air, the lean mixture having a lower equivalence ratio than the rich mixture; a wall coupled with the combustor liner; a rich fluid passage fluidly coupled to the rich fuel supply to emit the rich mixture into the combustion chamber; and a lean fluid passage fluidly coupled to the lean fuel supply to emit the lean mixture into the combustion chamber.