Dual-Fuel Combustor Nozzle for Flame-Stable Gas Turbine Mixing
Find Innovative SolutionsGenerate Solutions
Solution Overview
Problem
Gas turbines using hydrogen fuel face reliability issues due to high combustion rates causing flame heating and degradation, and combustors with multiple tubes struggle with burning a variety of fuels, especially when hydrocarbon-based fuels are injected at excessive speeds leading to flame escape.
Innovation Solution
A combustor nozzle design with separate fuel supply members for hydrogen-based and hydrocarbon-based fuels, where the hydrogen-based fuel is injected centrally and hydrocarbon-based fuel is injected along the inner circumferential wall, stabilizing the flame and controlling combustion characteristics.
Engineering Contradictions & Design Principles
Engineering Contradiction Analysis
1Productivity
If multiple mixing tubes are used to increase fuel injection speed for hydrogen combustion, then combustion efficiency is improved, but flame stability deteriorates causing flame escape
Solution Approach 1:
The nozzle is divided into multiple mixing tubes (at least three) with different injection speeds. Hydrogen-based fuel is injected through mixing tubes with higher injection speeds for efficient combustion, while hydrocarbon-based fuel is injected through mixing tubes with lower injection speeds to maintain flame stability and prevent flame escape.
Solution Approach 2:
Different regions of the nozzle (different mixing tubes) are assigned different injection speeds based on the fuel type. The injection speed is locally optimized: higher for hydrogen-based fuels to improve combustion efficiency, and lower for hydrocarbon-based fuels to maintain flame stability.
2Device complexity
If single fuel supply system is used, then device complexity is reduced, but adaptability to different fuel types deteriorates
Solution Approach 1:
The nozzle is designed with multi-functionality to handle different fuel types (hydrogen-based and hydrocarbon-based fuels) through the same nozzle structure. Multiple fuel supply members and multiple mixing tubes with different injection speeds enable the nozzle to adapt to various fuel types without requiring separate nozzles for each fuel type.
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 maintains stable combustion for a range of fuels, reducing vibration and emissions of carbon monoxide and nitrogen oxides by controlling fuel flow rates and ensuring uniform mixing.
Implementation Method 1
a plurality of mixing tubes through which air and fuel flow
Implementation Method 2
a first fuel supply member supplying the first fuel into each mixing tube; and a second fuel supply member supplying the second fuel into each mixing tube
Implementation Method 3
The combustor serves to mix compressed air from the compressor and fuel and combust the mixture of compressed air and fuel to produce combustion gases
Data Source
AI summary
A combustor nozzle includes a plurality of mixing tubes through which air and fuel flow, an accommodation tube accommodating and supporting the plurality of mixing tubes therein, a first fuel tube coupled to the accommodation tube to supply a first fuel into the accommodation tube, a second fuel tube coupled to the accommodation tube to supply a second fuel into the accommodation tube, a first fuel supply member supplying the first fuel into each mixing tube, and a second fuel supply member supplying the second fuel into each mixing tube.