Fuel Spray Nozzle Split for Lower nvPM in SAF Combustion
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Solution Overview
Problem
Gas turbine engines emit varying amounts of non-volatile particulate matter (nvPM) depending on the type and properties of the fuel used, necessitating adjustments in operating methods to reduce emissions.
Innovation Solution
The gas turbine engine is configured with a combustor featuring distinct subsets of fuel spray nozzles, optimized for different fuel flow rates, and operates using sustainable aviation fuel (SAF) to control nvPM emissions, defined by specific emissions index ratios and fuel flow rates.
Engineering Contradictions & Design Principles
Engineering Contradiction Analysis
1Object-generated harmful factors
If traditional kerosene-based jet fuel is used, then the gas turbine engine operates with established performance characteristics, but non-volatile particulate matter emissions increase
Solution Approach 1:
The patent adjusts operating parameters including fuel flow rate distribution between subsets of nozzles, equivalence ratio, and combustion temperature to optimize nvPM emissions when using SAF. This involves changing the operational parameters of the engine to match the specific properties of sustainable aviation fuel, thereby reducing harmful emissions while maintaining adaptability to different fuel types
Solution Approach 2:
The patent employs dynamic control of fuel flow rates to different nozzle subsets based on operating conditions and fuel type. The fuel flow distribution is adjusted in real-time to optimize combustion efficiency and minimize nvPM emissions, allowing the engine to adapt dynamically between traditional and sustainable fuels
2Object-generated harmful factors
If fuel flow rate to subsets of nozzles is equalized, then device complexity is reduced, but nvPM emissions cannot be optimized
Solution Approach 1:
The fuel spray nozzle system is divided into multiple subsets, each receiving different fuel flow rates optimized for specific combustion zones. This segmentation allows independent control of fuel distribution to different regions of the combustor, enabling precise optimization of combustion efficiency and nvPM emissions reduction
Solution Approach 2:
Different subsets of fuel spray nozzles are provided with different fuel flow rates tailored to local combustion requirements. This creates non-uniform fuel distribution patterns that optimize combustion in different zones, reducing nvPM emissions while maintaining overall engine performance
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 nvPM emissions, minimizing soot deposits, contrail formation, and environmental impact, 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
Data Source
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AI summary
A gas turbine engine for an aircraft. 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. An MTO nvPM emissions index ratio-modified fuel flow is defined as: EImaxTO,SAFEImaxTO,FF×Wf,maxTO 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); 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; and Wf,maxTO is the mass flow rate of fuel provided to the plurality of fuel spray nozzles (124) in kg/s when the gas turbine engine (10) is operating at around 100% available thrust for the given operating conditions. The MTO nvPM emissions index ratio-modified fuel flow of the gas turbine engine (10) in kg/s is less than 4. 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.