Staged Combustor Layout for Low-NOx Turbine Combustion
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Solution Overview
Problem
Turbine engines using hydrocarbon fuels or hydrogen-based fuels face challenges in reducing NOx emissions while maintaining efficiency, due to high combustor flame temperatures and undesirable by-products.
Innovation Solution
A combustion section with a primary combustor and a set of secondary combustors, where secondary exhaust gases are directed into the primary combustor at different orientations, reducing oxygen levels and temperatures to lower NOx emissions.
Engineering Contradictions & Design Principles
Engineering Contradiction Analysis
1Speed
If hydrogen or hydrogen mixed fuel is used for combustion, then burning velocity and flammable range are improved, but flame temperature increases leading to higher NOx emissions
Solution Approach 1:
The combustor is divided into multiple zones with different fuel injection points and combustion characteristics. Primary fuel is injected at the center and secondary fuel is injected at the periphery, creating segmented combustion regions that control flame temperature distribution and reduce peak temperatures to lower NOx emissions
Solution Approach 2:
Different regions of the combustor are given different fuel-air mixture qualities. The central region has a rich mixture while the peripheral region has a lean mixture, creating local variations in combustion intensity and temperature that allow high burning velocity in the center while controlling overall NOx formation through cooler peripheral zones
2Use of energy by moving object
If high combustor flame temperature is maintained for efficiency, then energy conversion is improved, but NOx emissions increase due to high temperature combustion
Solution Approach 1:
The combustion process is segmented into primary combustion zone for efficient energy release and secondary zones for temperature control. This allows maintaining high combustion efficiency in the primary zone while using secondary fuel injection to modulate temperatures and reduce NOx in downstream regions
Solution Approach 2:
The fuel-air equivalence ratio is varied spatially throughout the combustor. Rich mixtures (φ>1) are used in the primary combustion zone to maximize energy release, while lean mixtures (φ<1) are used in secondary zones to control peak temperatures and reduce NOx emissions, achieving both efficiency and emission control
3Device complexity
If traditional single combustor design is used, then device complexity is low, but temperature distribution is insufficient leading to higher pollutant emissions
Solution Approach 1:
The single combustor is segmented into multiple combustion zones with separate fuel injection systems. Primary fuel injectors are positioned at the center while secondary fuel injectors are positioned at the periphery, creating distinct combustion regions that improve temperature distribution and reduce pollutant emissions without requiring multiple separate combustors
Solution Approach 2:
The secondary fuel injection system is nested within the primary combustor structure. The secondary fuel injectors are positioned concentrically around the primary fuel injection point, allowing the secondary combustion zone to nest within the overall combustor volume and achieve improved emission control without significantly increasing external dimensions
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 arrangement of secondary combustors with angled exhausts and staged fueling reduces NOx emissions by improving temperature distribution and completing combustion, achieving lower pollutant levels while maintaining efficiency.
Implementation Method 1
The secondary combustors are arranged to exhaust gasses into the primary combustor... generating secondary exhaust gasses in a set of secondary combustors... The secondary exhaust gasses are introduced into the primary combustion chamber
Data Source
AI summary
A turbine engine with a compressor section, a combustion section, and a turbine section in serial flow arrangement along an engine centerline. A combustion section for the turbine engine, having a primary combustor liner including an inner liner and an outer liner annular about an engine centerline. A dome wall extending between the inner liner and the outer liner. A set of primary dome inlets located in the dome wall and circumferentially arranged about the engine centerline. A set of secondary combustors fluidly coupled to a primary combustion chamber, the set of secondary combustors including a first mini combustor and a second mini combustor.


