Integrated Combustor Nozzle for Gas Turbine Emissions Control
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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 maintaining emissions compliance across the full range of operation, particularly in reducing NOx and CO emissions.
Innovation Solution
A segmented annular combustion system with integrated combustor nozzles that include a fuel injection panel and a turbine nozzle, forming a seamless structure with inner and outer liner segments, which allows for axially staged fuel injection and reduces the need for seals, thereby enhancing combustion efficiency and emissions control.
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 control becomes difficult across full operation range
Solution Approach 1:
The patent combines the combustor nozzle and turbine nozzle into a single integrated structure. This merging eliminates the need for separate seals and multiple components, simplifying airflow balancing while maintaining complete combustion efficiency across the full operation range.
Solution Approach 2:
The integrated combustor nozzle serves multiple functions: it performs fuel injection, mixing, combustion support, and turbine blade cooling simultaneously. This multi-functionality reduces the number of separate components needed and simplifies the overall airflow balancing requirements.
2Adaptability or versatility
If multiple separate combustor components are used, then airflow can be directed to different zones, but the number of seals and assembly complexity increases
Solution Approach 1:
The patent merges the combustor nozzle and turbine nozzle into one integrated component, eliminating multiple seals and joints while maintaining the ability to direct airflow to different zones through internal passage design.
Solution Approach 2:
The integrated nozzle contains internal segmentation with separate passages for cooling air and combustion air, allowing flexible airflow distribution to different zones without requiring multiple external components or seals.
3Ease of manufacture
If conventional combustor nozzles with seals are used, then assembly is possible, but leakage paths and maintenance requirements increase
Solution Approach 1:
By integrating the combustor nozzle and turbine nozzle into a single piece, the patent eliminates multiple seals and joints that would create leakage paths, thereby improving reliability while maintaining assembly capability 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
The system effectively reduces NOx and CO emissions by optimizing fuel-air mixing and combustion dynamics, improving operational flexibility and reducing the complexity and cost of assembly.
Implementation Method 1
mixing channels defined within the fuel injection panel between the pressure side wall and the suction side wall
Implementation Method 2
a plurality of fuel injection lances configured to extend into the premix air plenum
Implementation Method 3
Industrial gas turbine combustion systems usually burn hydrocarbon fuels and produce air polluting emissions
Implementation Method 4
Oxidization of molecular nitrogen in the gas turbine depends upon the temperature of gas located in a combustor
Implementation Method 5
cooling passages extending through the turbine nozzle
Implementation Method 6
Cooling air is directed through a plurality of cooling passages defined within the integrated combustor nozzle
Data Source
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AI summary
The present disclosure is directed to an integrated combustor nozzle for a segmented annular combustion system. The integrated combustor nozzle includes an outer liner segment, an inner liner segment, and a fuel injection panel extending radially between the outer liner segment and the inner liner segment. The fuel injection panel includes a first side wall, a second side wall, and a plurality of premixing channels between the first and second side walls, each of the premixing channels having an outlet on one of the first and second side walls. The aft end of the fuel injection panel defines a turbine nozzle.