Segmented Combustor Nozzle Mounting for Gas Turbine Emissions
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Solution Overview
Problem
Conventional axially staged fuel injection combustion systems in gas turbines face challenges in balancing airflow for cooling and emissions compliance across the full range of operation, leading to inefficiencies and increased air polluting emissions like NOx and CO.
Innovation Solution
A segmented annular combustion system with integrated combustor nozzles, featuring fuel injection panels with premixing channels and a seamless integration with turbine nozzles, which includes a mounting system using double bellows seals and hooks for secure attachment, allowing for axial and radial movement, and independent fuel supply to each nozzle for optimized combustion.
Engineering Contradictions & Design Principles
Engineering Contradiction Analysis
1Productivity
If conventional axially staged fuel injection combustion systems are used, then complete combustion of fuel is achieved, but airflow balancing for cooling and emissions compliance becomes difficult across full operation range
Solution Approach 1:
The combustion system is divided into multiple independent combustor nozzles arranged circumferentially, each capable of receiving independent fuel supply. This segmentation allows individual control of airflow and fuel injection for each nozzle, enabling precise airflow balancing across the full operation range while maintaining complete combustion efficiency.
2Productivity
If conventional combustor designs are used, then combustion function is provided, but air polluting emissions like NOx and CO increase
Solution Approach 1:
Fuel is pre-mixed with air in premixing channels within each combustor nozzle before combustion occurs. This preliminary mixing action ensures complete combustion and reduces air polluting emissions such as CO and unburned hydrocarbons, while the controlled premixing process helps limit NOx formation by preventing localized high-temperature zones.
3Productivity
If integrated combustor nozzles with seamless integration are used, then combustion efficiency is enhanced, but mounting complexity increases
Solution Approach 1:
The combustor nozzle is seamlessly integrated with the turbine nozzle, combining the combustion function with the turbine inlet structure. This merging eliminates the need for separate mounting components and complex alignment procedures, reducing mounting complexity while maintaining enhanced combustion efficiency through the integrated design.
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
This design enhances the combustion efficiency by ensuring balanced airflow and reduced emissions, improving the turndown capability and operational flexibility of gas turbines while minimizing NOx and CO production.
Implementation Method 1
The outer surface of the outer liner segment proximate to the turbine nozzle may be attached to the outer mounting ring via a double bellows seal or a leaf seal... The double bellows seal is able to accommodate movement in the axial and radial directions
Implementation Method 2
Each fuel injection panel is provided with a plurality of premixing channels therein to receive fuel from the plurality of fuel injection lances and to introduce fuel into a secondary combustion zone
Implementation Method 3
Industrial gas turbine combustion systems usually burn hydrocarbon fuels and produce air polluting emissions such as oxides of nitrogen (NOx) and carbon monoxide (CO)
Implementation Method 4
Oxidization of molecular nitrogen in the gas turbine depends upon the temperature of gas located in a combustor, as well as the residence time for reactants located in the highest temperature regions within the combustor
Data Source
AI summary
A segmented annular combustion system includes integrated combustor nozzles, each of which has a fuel injection panel disposed radially between an inner liner segment and an outer liner segment. An aft end portion of the fuel injection panel defines a turbine nozzle. One or more hook plates attached to the outer surfaces of the liner segments are used to mount the integrated combustor nozzle to an inner mounting ring or an outer mounting ring. A mounting strut or mounting tenon(s) attached to the liner segments may also be employed.