RQL Combustor Nozzle Layout for Lower nvPM on Sustainable Aviation Fuel
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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 use of a rich burn, quick quench, lean burn (RQL) combustor with specific fuel spray nozzle configurations and the provision of sustainable aviation fuel (SAF) to optimize nvPM emissions, defined by various emissions index ratios and fuel flow parameters, reduces nvPM emissions across different operational conditions.
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, but non-volatile particulate matter emissions increase
Solution Approach 1:
The patent applies parameter changes by adjusting combustor operating parameters (equivalence ratio, temperature, pressure) when switching between different fuel types. The system modifies combustion parameters to optimize performance and minimize nvPM emissions for each specific fuel composition, enabling adaptive operation across diverse sustainable aviation fuel variants while maintaining low emissions.
Solution Approach 2:
The patent implements dynamics through real-time monitoring and adjustment of combustion parameters based on fuel properties and operating conditions. The combustor system dynamically adapts its operation to maintain optimal nvPM emissions levels regardless of fuel type variations or flight phase changes, transforming a static emission problem into a dynamically controllable process.
2Object-generated harmful factors
If combustor operating parameters are adjusted to reduce nvPM emissions, then environmental impact decreases, but engine performance may be compromised
Solution Approach 1:
The patent applies local quality by creating distinct combustion zones with different equivalence ratios - a fuel-rich primary zone for efficient combustion and a fuel-lean secondary zone for low nvPM emissions. This spatial differentiation of combustion conditions allows the engine to maintain high power output in the primary zone while minimizing emissions in the secondary zone, resolving the contradiction between performance and environmental impact.
Solution Approach 2:
The combustor is segmented into multiple functional zones with different operating characteristics. By dividing the combustion process into distinct stages (fuel-rich premixing, controlled combustion, fuel-lean quenching), the system achieves both high power generation in the combustion zone and low nvPM emissions in the quenching zone, eliminating the need to sacrifice performance for emission reduction.
3Productivity
If fuel spray nozzle configuration is optimized for specific fuel types, then combustion efficiency improves, but adaptability to different fuel compositions decreases
Solution Approach 1:
The fuel spray nozzle system is designed with universal multi-functionality, capable of effectively atomizing and distributing various sustainable aviation fuel types including HEFA, PtL, and algae-based fuels. The nozzle configuration uses adjustable parameters and versatile spray patterns that maintain high combustion efficiency across different fuel compositions without requiring dedicated nozzles for each fuel type, thus achieving both efficiency and adaptability.
Solution Approach 2:
The fuel spray system incorporates dynamic adjustability in spray patterns, droplet size distribution, and injection timing based on detected fuel properties and operating conditions. This dynamic adaptation allows the same nozzle configuration to optimize combustion efficiency for different fuel compositions, eliminating the trade-off between specialization and versatility.
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 dispersion time, thereby minimizing environmental impact and enhancing operational efficiency.
Implementation Method 1
a rich burn, quick quench, lean burn (RQL) combustor
Data Source
AI summary
A gas turbine engine includes: a rich burn, quick quench, lean burn combustor having a number of fuel spray nozzles in the range of 14-22 or a number of fuel spray nozzles per unit engine core size in the range 2 to 6. An MTO nvPM emissions index ratio is defined as:EImaxTO,SAFEImaxTO,FFwhere: EImaxTO,SAF and EImaxTO,FF are respectively the nvPM emissions index in mg/kg of the gas turbine engine when operating at around 100% available thrust for the given operating conditions if a fuel provided to the fuel spray nozzles includes a sustainable aviation fuel (SAF) or is a fossil-based hydrocarbon fuel. The MTO nvPM emissions index ratio of the gas turbine engine is less than 1. The gas turbine engine is configured to provide fuel including a SAF to the fuel spray nozzles. Also disclosed is a method of operating a gas turbine engine.