Combustor Nozzle Fuel Split for Lower Gas Turbine nvPM Emissions
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Solution Overview
Problem
Gas turbine engines emit varying amounts of non-volatile particulate matter (nvPM) depending on the fuel type and operating parameters, necessitating adjustments in operating methods to reduce undesirable emissions and environmental impact.
Innovation Solution
The gas turbine engine is configured with specific fuel spray nozzle arrangements and operates using sustainable aviation fuel (SAF), optimizing fuel distribution and combustion to achieve reduced nvPM emissions indices through defined ratios and fuel flow rates.
Engineering Contradictions & Design Principles
Engineering Contradiction Analysis
1Object-generated harmful factors
If traditional kerosene-based jet fuel is used in gas turbine engines, then the engine can operate with established fuel infrastructure and compatibility, but it produces higher non-volatile particulate matter (nvPM) emissions and soot deposits
Solution Approach 1:
The patent changes the chemical composition parameters of the fuel by introducing sustainable aviation fuel (SAF) with different molecular structures and properties compared to traditional kerosene. This parameter change reduces nvPM emissions while the patent simultaneously addresses compatibility issues through adjusted combustion parameters and engine operating conditions.
2Object-generated harmful factors
If fuel flow rate distribution is optimized to reduce nvPM emissions, then environmental impact is reduced, but combustion efficiency and thrust production may be affected
Solution Approach 1:
The patent applies local quality by creating different fuel flow rate distributions across different zones of the combustor. Specific nozzles receive different fuel flow rates based on their location and function, optimizing combustion in each zone to simultaneously reduce nvPM emissions and maintain thrust production. The ratio of nozzles in first subset to second subset (1:3 to 1:6) creates localized combustion characteristics that balance emissions and power.
3Object-generated harmful factors
If fuel spray nozzle configuration is modified to achieve specific emission ratios, then nvPM emissions are reduced, but device complexity increases
Solution Approach 1:
The patent segments the fuel spray nozzle system into two distinct subsets: a first subset of nozzles receiving higher fuel flow rates and a second subset receiving lower fuel flow rates. This segmentation (with ratios of 1:3 to 1:6) allows independent optimization of different combustion zones, achieving reduced nvPM emissions through differentiated fuel distribution while maintaining manageable system complexity through clear functional grouping.
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 configuration leads to reduced soot deposits, improved local air quality, and decreased contrail formation and dispersal time, particularly at idle and cruise conditions, thereby minimizing environmental impact.
Implementation Method 1
a plurality of fuel spray nozzles configured to inject fuel into the combustion chamber
Implementation Method 2
a combustor, comprising a combustion chamber and a plurality of fuel spray nozzles configured to inject fuel into the combustion chamber
Data Source
AI summary
A gas turbine engine includes a combustor with a combustion chamber and fuel spray nozzles to inject fuel into the combustion chamber. The nozzles include a first and second subset. Each of the nozzles of the first subset is supplied with fuel at a greater rate than each of the second subset. A ratio of nozzles in the first subset to nozzles in the second subset from 1:3 to 1:6. A fuel-flow nvPM emissions index ratio isEIidle×Wf,idleRImaxTO×Wf,maxTO.EIidle and EImaxTO are the system loss corrected nvPM emissions index in mg/kg operating at around 7% and 100% available thrust for the given operating conditions, respectively. Wf,idle and Wf,maxTO are the rate of fuel flow to the fuel spray nozzles in kg/s at around 7% and 100% available thrust for the given operating conditions, respectively. The fuel-flow nvPM emissions index ratio of the gas turbine engine is less than 0.3.