Fuel Nozzle Vortex Generator Structure for Hydrogen Flashback Control
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Solution Overview
Problem
Turbine engines using hydrogen fuel face challenges with flashback and flame spread due to the high burn rate and instability of hydrogen, leading to improper mixing with compressed air, which can result in ignition within the fuel nozzle.
Innovation Solution
A fuel nozzle design incorporating a support matrix with vortex generators to enhance turbulence and mixing of hydrogen-containing fuels with compressed air, ensuring stable combustion.
Engineering Contradictions & Design Principles
Engineering Contradiction Analysis
1Object-generated harmful factors
If hydrogen fuel is used in the combustor, then carbon emissions are reduced, but flashback and flame spread occur due to high burn rate and instability
Solution Approach 1:
The patent introduces a support matrix as an intermediary structure within the fuel nozzle that provides a framework for stable combustion. The matrix supports the flame front and prevents uncontrolled flashback by providing a structured pathway for combustion, thereby enabling hydrogen fuel use while maintaining combustion stability.
Solution Approach 2:
The patent modifies the combustion parameters by introducing a support matrix that changes the flow dynamics and combustion characteristics. The matrix alters the local velocity, pressure, and temperature distribution, creating conditions that stabilize hydrogen combustion and prevent flashback while maintaining efficient burning.
2Object-generated harmful factors
If hydrogen fuel is used without diluents, then carbon emissions are lowered, but improper mixing with compressed air occurs leading to ignition within the fuel nozzle
Solution Approach 1:
The support matrix segments the fuel nozzle internal flow path into multiple channels and zones. This segmentation creates numerous small-scale mixing regions where hydrogen and compressed air can interact more effectively, improving mixing efficiency and preventing improper combustion within the nozzle.
Solution Approach 2:
The support matrix introduces a spatial dimension to the mixing process by providing a three-dimensional structure within the nozzle. This dimensional addition creates multiple flow paths and interaction zones, enhancing the mixing between fuel and air before combustion occurs.
3Ease of operation
If a support matrix with vortex generators is added to the fuel nozzle, then fuel-air mixing is improved, but device complexity increases
Solution Approach 1:
The vortex generators on the support matrix create self-induced turbulence and vortices that automatically enhance mixing without requiring external control mechanisms. The structure serves its own purpose of improving fuel-air mixing through the natural flow dynamics generated by the vortex elements.
Solution Approach 2:
The patent utilizes the pneumatic properties of the flowing gases to create mixing enhancement. The vortex generators harness the kinetic energy and flow characteristics of the compressed air and hydrogen to generate beneficial turbulence and mixing patterns, converting flow energy into improved combustion efficiency.
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 stabilizes the combustion process by generating vortices that improve fuel-air mixing, reducing the risk of flashback and flame spread, while allowing for the use of hydrogen fuel without diluents, thereby lowering carbon emissions.
Implementation Method 1
A compressed air flow is fed to a fuel nozzle channel, over a support matrix and over a set of vortex generators. The vortex generators increase the capability of a flow of fuel to be mixed with the compressed air within the fuel nozzle by generation of vortices.
Implementation Method 2
The vortex generators increase the capability of a flow of fuel to be mixed with the compressed air within the fuel nozzle by generation of vortices.
Data Source
AI summary
A gas turbine engine including a compressor section, a combustion section, and a turbine section in a serial flow arrangement, with the combustion section having a fuel nozzle including a fuel nozzle body defining an axis and having an inner surface defining a channel fluidly coupled to a combustion chamber, a support matrix located within the channel comprising a plurality of segments which intersect each other when viewed from aft, and a set of vortex generators located on the support matrix.