Dual-Zone Multi-Fuel Combustor for Lower-NOx Turbine Operation
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Solution Overview
Problem
Turbine engines face challenges in efficiently utilizing multiple fuel types and reducing emissions, particularly nitrogen oxides (NOx), especially during varying operational phases.
Innovation Solution
A multi-fuel combustion system with a rotary fuel slinger for liquid fuel and a gaseous fuel injector for hydrogen or other gases, allowing for efficient mixing and combustion in separate zones, with the second combustion zone utilizing hydrogen for faster, cleaner burning to reduce emissions.
Engineering Contradictions & Design Principles
Engineering Contradiction Analysis
1Object-generated harmful factors
If a single combustion zone uses traditional liquid fuel, then the system is simpler to operate, but emissions particularly NOx are higher and combustion efficiency is lower
Solution Approach 1:
The combustion system is divided into two separate combustion zones: a first combustion zone that burns liquid fuel (aviation turbine fuel) and a second combustion zone that burns gaseous fuel (hydrogen). This segmentation allows each zone to be optimized for its specific fuel type, with the second zone specifically designed to reduce emissions from the first zone's combustion process.
Solution Approach 2:
The system changes the fuel parameter from single-phase liquid fuel to a two-phase combination of liquid and gaseous fuel. The gaseous fuel (hydrogen) has different combustion characteristics including higher flame speed and lower emissions, which when introduced in the second combustion zone, transforms the overall emission profile of the system.
2Adaptability or versatility
If traditional single-fuel system is used, then the device complexity is lower, but adaptability to different fuel types and operational phases is reduced
Solution Approach 1:
The combustion system is designed with multi-functionality to handle different fuel types and operational phases. The first fuel system can supply liquid aviation turbine fuel while the second fuel system can supply gaseous hydrogen or other gaseous fuels. The control system can selectively activate different fuel systems based on operational requirements, providing universal adaptability across various flight conditions.
Solution Approach 2:
The fuel system is designed to be dynamic and adjustable during operation. The control system can vary the amount and type of fuel supplied to each combustion zone based on real-time operational phases (start-up, idle, cruise, descent, landing). This dynamic capability allows the system to optimize performance and emissions for each specific operational condition.
3Object-generated harmful factors
If exhaust from first combustion zone is burned in second combustion zone with gaseous fuel, then emissions are reduced, but the combustion process becomes more complex
Solution Approach 1:
The system converts the harmful exhaust gases from the first combustion zone into a beneficial resource for the second combustion zone. The exhaust containing unburned hydrocarbons and carbon monoxide is routed to the second combustion zone where it is burned with gaseous fuel, transforming these harmful emissions into additional heat energy that contributes to overall system efficiency while further reducing total emissions.
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 system enhances combustion efficiency and reduces emissions, particularly NOx, by optimizing fuel use across different operational phases, including start-up, idle, cruise, descent, and landing, while accommodating various fuel availability.
Implementation Method 1
The rotary fuel slinger is rotationally driven and can atomize the first fuel received by rapid spinning and spraying of the first fuel. That is, the first fuel can be centrifuged radially outward within a portion of the rotary fuel slinger
Implementation Method 2
air and fuel are fed to a combustion chamber, the air and fuel are mixed, and then the fuel is burned in the presence of the air to produce hot gas
Implementation Method 3
The second fuel burns faster, hotter, cleaner or any combination thereof when compared to the first fuel
Data Source
AI summary
A multi-fuel combustion system for a turbine engine, the multi-fuel combustion system having a combustion chamber formed by a combustor liner. The combustion chamber defines a first combustion zone and a second combustion zone. A first fuel system is fluidly coupled with the first combustion zone, where a rotary fuel slinger provides a first fuel to the first combustion zone. A second fuel system is fluidly coupled with the second combustion zone, where a gaseous fuel injector provides a second fuel to the second combustion zone.