Combustor Nozzle Flow Split for Lower SAF Particulate Emissions
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Solution Overview
Problem
Gas turbine engines emit non-volatile particulate matter (nvPM) emissions are sensitive to the type and properties of fuel used, necessitating adjustments in operating parameters and configurations to optimize performance and reduce emissions, particularly for sustainable aviation fuel (SAF).
Innovation Solution
The gas turbine engine is configured with a combustor having a combustion chamber and a plurality of fuel spray nozzles, which a plurality of fuel spray nozzles, which a first subset of fuel spray nozzles and a second subset of fuel spray nozzles, with varying fuel flow rates and ratios, to inject fuel into the combustion chamber, optimizing the distribution, ignition, and combustion of sustainable aviation fuel (SAF).
Engineering Contradictions & Design Principles
Engineering Contradiction Analysis
1Object-affected harmful factors
If traditional kerosene-based jet fuel is used in gas turbine engines, then the engine operates with established performance characteristics, but non-volatile particulate matter (nvPM) emissions increase and environmental impact worsens
Solution Approach 1:
The patent adjusts combustion parameters including fuel spray nozzle configuration (dividing nozzles into subsets with different flow rates), fuel injection timing, and air-fuel ratio to optimize combustion characteristics when using SAF, thereby reducing nvPM emissions while maintaining engine performance
Solution Approach 2:
The fuel spray nozzles are divided into a first subset and a second subset with different fuel flow rates, creating segmented injection zones that improve fuel atomization and combustion efficiency for SAF, leading to reduced particulate matter emissions
2Object-affected harmful factors
If fuel properties are changed to use sustainable aviation fuel (SAF), then environmental impact is reduced, but engine performance and emissions characteristics become sensitive and require operational adjustments
Solution Approach 1:
The patent implements operational adjustments based on monitored combustion parameters and emissions output, dynamically tuning fuel injection and air supply to maintain stable nvPM emissions when using SAF, ensuring consistent performance across varying flight conditions
3Object-generated harmful factors
If fuel flow rate distribution is optimized to reduce nvPM emissions, then soot deposits and contrail formation are reduced, but combustion efficiency and power output may be affected
Solution Approach 1:
Different regions of the combustion chamber receive fuel at different flow rates through the first and second subsets of nozzles, creating localized optimization zones where fuel-rich areas reduce soot formation while fuel-lean areas maintain combustion efficiency and power output
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 reduces non-volatile particulate matter (nvPM) emissions, minimizing soot deposits, contrail formation, and improving local air quality, particularly at idle and cruise conditions, and reducing 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... configured to inject fuel into the combustion chamber
Data Source
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AI summary
A gas turbine engine (10) for an aircraft is disclosed. The gas turbine engine (10) comprises: a combustor (16), comprising a combustion chamber (120) and a plurality of fuel spray nozzles (124) configured to inject fuel into the combustion chamber (120), wherein the plurality of fuel spray nozzles (124) comprises a first subset (124A) of fuel spray nozzles (124) and a second subset (124B) of fuel spray nozzles (124), wherein the combustor (16) is operable in a condition in which each of the fuel spray nozzles of the first subset (124A) of fuel spray nozzles (124) is supplied with fuel at a greater fuel flow rate than each of the fuel spray nozzles of the second subset (124B) of fuel spray nozzles (124), wherein a ratio of the number of fuel spray nozzles (124) in the first subset (124A) of fuel spray nozzles (124) to the number of fuel spray nozzles (124) in the second subset (124B) of fuel spray nozzles (124) is in the range of 1:3 to 1:6. A MTO nvPM emissions index ratio is defined as: EImaxTO,SAFEImaxTO,FF where: EImaxTO,SAF is the system loss corrected nvPM emissions index in mg/kg of the gas turbine engine (10) when operating at around 100% available thrust for given operating conditions if a fuel provided to the plurality of fuel spray nozzles (124) comprises a sustainable aviation fuel (SAF); and EImaxTO,FF is the system loss corrected nvPM emissions index in mg/kg of the gas turbine engine (10) when operating at around 100% available thrust for the given operating conditions if a fuel provided to the plurality of fuel spray nozzles (124) is a fossil-based hydrocarbon fuel. The MTO nvPM emissions index ratio of the gas turbine engine (10) is less than 1. The gas turbine engine (10) is configured to provide fuel comprising a SAF to the plurality of fuel spray nozzles (124). Also disclosed are methods of operating the gas turbine engine.