Fuel Nozzle and Swirler Flow Control for Hydrogen Flashback
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Solution Overview
Problem
Turbine engines face durability risks due to flame holding and flashback issues when using high-temperature fuels like hydrogen, which burn hotter and faster, posing challenges for efficient combustion and emission reduction.
Innovation Solution
A fuel nozzle and swirler architecture designed to manage high-temperature fuels, featuring adjustable flow control mechanisms such as movable walls, rotating vanes, and perforated rings to regulate airflow and pressure drop, preventing flame holding and flashback.
Engineering Contradictions & Design Principles
Engineering Contradiction Analysis
1Productivity
If high-temperature fuels like hydrogen are used to improve combustion efficiency and reduce carbon emissions, then combustion efficiency and emission reduction are improved, but flame holding and flashback risks increase, reducing durability
Solution Approach 1:
The patent implements a movable wall within the swirler assembly that can dynamically adjust its position to control airflow characteristics. This dynamic adjustment allows the system to adapt to different operating conditions, optimizing combustion efficiency while preventing flame holding and flashback that would compromise durability. The movable wall changes the swirler's geometry in real-time, balancing the competing requirements of productivity and reliability.
Solution Approach 2:
The patent changes physical parameters of the fuel nozzle and swirler system, including adjustable flow control mechanisms that modify pressure drop and airflow rate. By varying these parameters, the system achieves efficient combustion of high-temperature fuels while maintaining safe operating margins that prevent flame propagation issues, thus resolving the contradiction between improved combustion efficiency and maintained durability.
2Object-generated harmful factors
If high-temperature fuels are used to reduce carbon emissions, then emission reduction is improved, but flame speed increases causing flashback risks
Solution Approach 1:
The patent applies preliminary anti-action by designing the swirler with a movable wall that creates predetermined airflow patterns and pressure distributions before combustion occurs. This pre-configured flow structure counteracts the high flame speed of hydrogen fuels, creating a protective effect that prevents flashback while allowing the benefits of reduced carbon emissions to be realized.
Solution Approach 2:
The movable wall and adjustable flow control mechanisms serve as intermediaries between the high-temperature fuel and the combustion chamber. These components mediate the interaction by controlling airflow and pressure, allowing efficient combustion and emission reduction while preventing the harmful effect of high flame speed from causing flashback.
3Reliability
If adjustable flow control mechanisms are added to prevent flame holding and flashback, then durability is improved, but device complexity increases
Solution Approach 1:
The patent merges the flow control function with the existing swirler assembly by integrating a movable wall into the swirler's structure. This combination allows the system to achieve durable operation through adjustable flow control without adding completely separate complex subsystems. The merged design reduces overall complexity while maintaining the reliability benefits of active flow management.
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
Enhances durability and efficiency of combustion by controlling flame behavior, ensuring stable operation with high-temperature fuels, thereby improving engine performance and reducing carbon emissions.
Implementation Method 1
A swirler provides for mixing the fuel with air in order to achieve efficient combustion
Implementation Method 2
The engine utilizes a fuel nozzle to inject the combustible fuel into the combustor
Data Source
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AI summary
A turbine engine can (10) include a compressor section (12), a combustion section (14), and a turbine section (16) in serial flow arrangement. The combustion section (14) can include a combustor (36, 636, 736) with a combustor liner (40), a dome assembly (44) coupled to the combustor liner (40), a fuel nozzle (54, 102) fluidly coupled to the dome assembly(44), a combustion chamber (5) fluidly coupled to the fuel nozzle (54, 102), and at least one set of dilution openings (60, 66, 68) located in the dome assembly (44) or combustor liner (40) that fluidly couple to the combustion chamber (50). A swirler (104, 204, 304) can define at least one passage 126, 128, 226, 228, 326, 328) extending between at least one annular entrance (134, 136, 234, 236, 334, 336, 635, 637) and at least one annular exit (147, 247, 347), wherein the at least one annular entrance (134, 136, 234, 236, 334, 336, 635, 637) is fluidly coupled to the compressor section (12). A variable area device (140, 142, 216, 370, 640, 642, 770, 773) is movable relative to the at least one set of dilution openings (60, 66, 68) or at least a portion of the swirler (104, 204, 304).