Hydrogen Combustor Nozzle Cooling Space and Mixing Guides
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Solution Overview
Problem
Gas turbines using hydrogen fuel face challenges with nozzle tip overheating and reliability due to high combustion rates, necessitating efficient cooling and uniform fuel-air mixing.
Innovation Solution
A combustor nozzle design featuring a multi-tube structure with a fuel tube, tip plate, and front plate that defines a cooling space, along with mixing guides for uniform air-fuel mixing, and a duct assembly for efficient combustion gas transmission.
Engineering Contradictions & Design Principles
Engineering Contradiction Analysis
1Object-generated harmful factors
If hydrogen fuel or fuel containing hydrogen is burned in a gas turbine combustor, then carbon dioxide emission is inhibited, but the flame approaches and heats the combustor structure causing reliability problems
Solution Approach 1:
The nozzle is divided into multiple segments including a main cylinder, nozzle shroud, and fuel injection module with multiple struts. This segmentation allows for targeted cooling of the nozzle tip part while maintaining the overall combustor structure integrity when burning hydrogen fuel
Solution Approach 2:
A coolant fluid is introduced as an intermediary substance between the hydrogen combustion process and the nozzle tip structure. The coolant absorbs excess heat from the flame, preventing direct heating of the combustor structure while allowing hydrogen combustion to proceed
2Object-generated harmful factors
If hydrogen fuel is burned in a gas turbine, then emission inhibition is achieved, but the nozzle tip part requires efficient cooling to prevent deterioration
Solution Approach 1:
Coolant fluid is supplied to the nozzle tip part in advance before the flame reaches maximum temperature. This preliminary cooling action prevents the nozzle tip from overheating during hydrogen combustion, allowing emission inhibition to proceed without structural deterioration
Solution Approach 2:
The high temperature flame from hydrogen combustion, which would normally harm the nozzle tip, is converted into a beneficial cooling mechanism. The coolant fluid absorbs the excessive thermal energy, and the cooled fuel then helps maintain appropriate combustion temperatures while protecting the nozzle structure
3Temperature
If a multi-tube structure with cooling space is implemented, then nozzle tip cooling is improved, but device complexity increases
Solution Approach 1:
The multi-tube structure serves multiple functions simultaneously: it provides fuel injection pathways, creates cooling spaces for coolant fluid circulation, and maintains structural support for the nozzle components. This multi-functionality reduces the need for separate dedicated cooling systems, thereby limiting the increase in device complexity
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 effectively cools the nozzle tip and ensures uniform mixing of hydrogen and air, enhancing the reliability and efficiency of the gas turbine by preventing overheating and optimizing combustion processes.
Implementation Method 1
a cooling space supplied with coolant fluid to cool the nozzle tip part
Implementation Method 2
mixing guides for uniform air-fuel mixing
Data Source
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AI summary
Disclosed herein is a nozzle(1400) for a combustor(1200) that burns fuel containing hydrogen, which includes a plurality of mixing tubes(1420) through which air and fuel flow, a multi-tube(1410) configured to contain and support the mixing tubes(1420), a fuel tube(1450) formed inside the multi-tube(1410) and through which fuel flows, a tip plate(1415) coupled to a tip of the multi-tube(1410), and a front plate(1460, 2460, 3460) spaced apart from the tip plate(1415) to define a cooling space(CS1).