Gas Turbine Combustor Segmented Fuel Nozzles Ignition
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Solution Overview
Problem
Gas turbine combustors face challenges in stably igniting hydrogen content fuels without hydrogen, leading to potential unburned fuel emission and reduced dispersibility, which affects NOx emissions and reliability.
Innovation Solution
A gas turbine combustor design with a startup fuel pipe, main fuel pipes, a fuel mixer, and control valves to mix and control the flow of startup and main fuels, ensuring stable ignition and dispersibility of hydrogen content fuels.
Engineering Contradictions & Design Principles
Engineering Contradiction Analysis
1Productivity
If a hydrogen content fuel is used in a gas turbine combustor, then the power generation efficiency and environmental friendliness are improved, but the risk of flashback and NOx emissions increase
Solution Approach 1:
The fuel supply system is segmented into multiple fuel nozzles with different functions: some nozzles are dedicated to startup fuel (natural gas) while others are dedicated to main fuel (hydrogen content fuel). This segmentation allows independent control of each fuel type, enabling stable ignition with startup fuel while maintaining good dispersibility with main fuel, thus resolving the contradiction between efficient hydrogen combustion and flashback prevention
Solution Approach 2:
A pilot burner is introduced as an intermediary device that first ignites startup fuel to create a stable flame source. This pilot flame then serves as the ignition source for the main hydrogen content fuel. The intermediary pilot burner ensures reliable ignition while the main fuel nozzles maintain optimal dispersibility, preventing both flashback and excessive NOx formation
2Object-affected harmful factors
If a lean combustion type combustor is used to reduce NOx emissions and prevent flashback, then the environmental performance and safety are improved, but the complexity of the fuel supply system increases
Solution Approach 1:
The fuel supply system is designed with multi-functionality: the same combustor structure can accommodate different fuel types (startup fuel and main fuel) through a coordinated system of fuel nozzles and control valves. The system universally handles both natural gas and hydrogen content fuels, achieving NOx reduction and flashback prevention without requiring entirely separate systems for each fuel type
Solution Approach 2:
The fuel supply system incorporates dynamic control through multiple control valves that can independently regulate the flow of startup fuel and main fuel. This dynamic control allows the system to adapt to different operating conditions, maintaining optimal performance while managing complexity through intelligent control rather than mechanical complexity
3Reliability
If startup fuel is used for ignition, then the reliability of ignition is improved, but the dispersibility of the main hydrogen content fuel deteriorates
Solution Approach 1:
The fuel nozzles are segmented into distinct groups: startup fuel nozzles optimized for reliable ignition of natural gas, and main fuel nozzles optimized for dispersibility of hydrogen content fuel. This segmentation ensures that each fuel type is delivered through nozzles designed for its specific requirements, preventing the deterioration of dispersibility that would occur if startup fuel nozzles were used for main fuel
4Productivity
If unburned hydrogen content fuel is emitted from the combustor, then the fuel efficiency is reduced, but the risk of turbine damage and emissions increases
Solution Approach 1:
The control system incorporates feedback mechanisms that monitor combustion conditions and adjust the fuel supply accordingly. This feedback control ensures complete combustion of the main hydrogen content fuel by detecting unburned fuel and adjusting the air-fuel ratio or ignition timing, preventing unburned fuel from reaching the turbine and causing damage while maintaining high fuel 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 enables stable ignition of hydrogen content fuels, preventing unburned fuel emission and enhancing dispersibility, thereby reducing NOx emissions and improving combustor reliability.
Implementation Method 1
a fuel mixer to which the startup fuel pipe and the first main fuel pipe are connected
Implementation Method 2
a startup fuel control valve provided in the startup fuel pipe; a first fuel control valve provided in the first main fuel pipe; and a second fuel control valve provided in the second main fuel pipe
Implementation Method 3
Gas turbine combustor and its operating method
Data Source
AI summary
A hydrogen content fuel can be stably ignited using a gaseous fuel that does not contain hydrogen and dispersibility of the hydrogen content fuel is enhanced.A gas turbine combustor including a burner including: a startup fuel pipe in which a startup fuel circulates; a first main fuel pipe in which a main fuel circulates, a second main fuel pipe in which the main fuel circulates; a fuel mixer to which the startup fuel pipe and the first main fuel pipe are connected; an inner fuel nozzle to which the fuel mixer is connected; a plurality of outer fuel nozzles to which the second main fuel pipe is connected; a startup fuel control valve provided in the startup fuel pipe; a first fuel control valve provided in the first main fuel pipe; and a second fuel control valve provided in the second main fuel pipe.