Combustor Nozzle Flow Distribution for Lower Aircraft 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 emissions.
Innovation Solution
The use of sustainable aviation fuel (SAF) in gas turbine engines, combined with specific combustor configurations and fuel spray nozzle arrangements, to optimize fuel distribution and combustion, thereby reducing nvPM emissions.
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 high nvPM emissions are produced
Solution Approach 1:
The patent changes the chemical composition parameters of the fuel by introducing sustainable aviation fuels (SAF) with different molecular structures and properties compared to traditional kerosene. This parameter change reduces nvPM emissions while the patent simultaneously adapts engine operating parameters (temperature, pressure, fuel flow rates) to maintain performance, thus resolving the contradiction between emission reduction and fuel flexibility.
2Object-generated harmful factors
If fuel operating parameters are adjusted to reduce nvPM emissions, then emissions are reduced, but engine performance and thrust may be compromised
Solution Approach 1:
The patent implements dynamic adjustment of fuel operating parameters including temperature, pressure, and flow rates through controlled fuel injection systems. The fuel is introduced at specific temperatures and pressures that optimize combustion efficiency while reducing nvPM formation. This dynamic control allows the engine to maintain required thrust levels while achieving emission reduction targets, resolving the contradiction between power output and emission control.
3Object-generated harmful factors
If sustainable aviation fuel is introduced to reduce emissions, then environmental impact is reduced, but fuel infrastructure and engine compatibility challenges arise
Solution Approach 1:
The patent segments the fuel system into distinct components: the sustainable aviation fuel supply system, the fuel injection system with controlled temperature and pressure regulation, and the combustion system. This segmentation allows each component to be optimized independently - the fuel supply can use SAF while the injection and combustion systems are tuned to handle SAF's specific properties, thus resolving infrastructure compatibility issues while maintaining emission reduction benefits.
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 approach leads to reduced nvPM emissions, minimizing soot deposits, contrail strength, and environmental impact, while improving local air quality and reducing emissions at different flight stages.
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 flow rate than each of the second subset. A ratio of nozzles in the first subset to the second subset is 1:2 to 1:5. An MTO nvPM emissions index ratio-modified fuel flow isEImaxTO, SAFEImaxTO, FF×Wf, maxTO.EImaxTO,SAF is nvPM emissions index in mg/kg of the engine operating at around 100% available thrust with sustainable aviation fuel. EImaxTO,FF is nvPM emissions index in mg/kg of the engine operating at around 100% available thrust with fossil-based hydrocarbon. Wf,maxTO is mass flow rate of fuel to the nozzles in kg/s operating at around 100% available thrust. The MTO nvPM emissions index ratio-modified fuel flow in kg/s is less than 2.