Hydrogen Combustor Nozzle Flame Stabilization
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Solution Overview
Problem
Hydrogen-containing fuels pose a challenge in gas turbines due to their high combustion rate, causing flames to approach and heat the combustor structure, reducing reliability, and maintaining a stable flame is difficult when hydrogen is injected at high speeds.
Innovation Solution
A combustor nozzle design featuring a first tube for fuel injection, a second tube for premixing with air, and a third tube with fine injection holes spaced circumferentially to form fine flames, which connect with the main flame, stabilizing it, and a fourth tube for cooling air to prevent thermal deterioration.
Engineering Contradictions & Design Principles
Engineering Contradiction Analysis
1Use of energy by moving object
If hydrogen-containing fuel is burned in the gas turbine combustor, then the combustion efficiency is improved, but the flame approaches the combustor structure and heats it, reducing reliability
Solution Approach 1:
The fuel injection system is segmented into multiple tubes with different functions: a first tube for main fuel injection, a second tube for air premixing, and a third tube for additional fuel injection with fine injection holes. This segmentation allows separate control of fuel delivery and air mixing, enabling the flame to be positioned away from the combustor structure while maintaining combustion efficiency
Solution Approach 2:
The second tube acts as an intermediary by introducing air for premixing with fuel before combustion. This creates a controlled fuel-air mixture that burns more cleanly and positions the flame further from the combustor walls, reducing thermal loading on the structure while maintaining efficient energy release
2Reliability
If hydrogen is injected at high speed to move the flame away from the combustor structure, then the combustor reliability is improved, but the flame becomes unstable and difficult to maintain
Solution Approach 1:
The system merges multiple fuel injection mechanisms: the first tube provides main fuel flow, the third tube with fine injection holes provides additional fuel, and the second tube provides air premixing. This combination allows the flame to be stabilized through controlled mixing and multiple injection points, maintaining reliability without requiring excessive injection speeds that would destabilize the flame
Solution Approach 2:
Different regions of the nozzle system have specialized functions: the first tube handles main fuel delivery, the second tube creates a premixing zone for controlled combustion, and the third tube with fine holes creates localized fine flames. This local differentiation allows each zone to contribute to flame stability while maintaining the flame position away from the combustor structure
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 nozzle design effectively maintains a stable flame by forming fine flames that protect the main flame, preventing flashback and ensuring reliable operation of the gas turbine combustor.
Implementation Method 1
a first tube through which the fuel flows and having a fuel injection hole on a front side to inject the fuel therethrough
Implementation Method 2
a second tube surrounding the first tube and having a premixing injection hole through which the fuel and air are mixed and discharged
Implementation Method 3
a third tube surrounding the second tube and through which the fuel flows, wherein the second tube includes a plurality of fine injection holes to inject the fuel from the third tube to form fine flames
Implementation Method 4
a fourth tube surrounding the third tube and through which a cooling air flows, wherein the fourth tube may include a plurality of air injection holes at the tip
Data Source
AI summary
A nozzle for a combustor burning a hydrogen-containing fuel is provided. The nozzle includes a first tube through which the fuel flows and having a fuel injection hole on a front side to inject the fuel therethrough, a second tube surrounding the first tube and having a premixing injection hole through which the fuel and air are mixed and discharged, and a third tube surrounding the second tube and through which the fuel flows, wherein the second tube includes a plurality of fine injection holes to inject the fuel from the third tube to form fine flames, and the fine injection holes are spaced apart from each other in a circumferential direction of the second tube.