Predicting Lean Blowout and Emissions of Aircraft Engine Combustion Chamber Based on CRN
-
Yinli Xiao
,
Zhengxin Lai
Abstract
To predict the pollutant emissions and lean blowout, chemical reactor network (CRN) model is applied to the modern aircraft engine combustion chamber. In this study, the CRN which represent the major features of aerodynamics and combustion in the combustion chamber is set up based on the OpenFOAM simulation results. The boundary and the initial conditions used for the CRN derive from the operating modes of typical aircraft engine cycle. A 21 species 30 steps chemical mechanism of kerosene is employed in the CRN method. The levels of pollutant emissions are obtained under four ICAO engine power settings of idle, approach climb and take off. The lean blowout equivalent ratio is evaluated at the idle power setting. The results will be helpful to predict the aircraft engine exhaust emissions and lean blowout (LBO).
Nomenclature
kerosene surface tension (N/m)
dynamic viscosity (Pa·s)
fuel mass flow rate (kg/s)
injector pressure difference (Pa)
gas conductivity (W/m·K)
the Spalding number
fuel density (kg/m3)
gas specific heat (kJ/kg·K)
pressure of the incoming air (Pa)
temperature of the incoming air (K)
standard deviation of Gaussian function
mixing parameter
mean equivalence ratio
- APU
Auxiliary Power Unit
- CARS
Coherent Anti-Stokes Raman Scattering
- CFD
Computational Fluid Dynamics
- CRN
Chemical Reactor Network
- EI
Emission Index
- ICAO
International Civil Aviation Organization
- LBO
Lean BlowOut
- LTO
Landing/Taking Off
- PFR
Plug Flow Reactor
- PSR
Perfect Stirred Reactor
- SMD
Sauter Mean Diameter
- UHC
Unburned Hydrocarbon
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Articles in the same Issue
- Frontmatter
- Editorial
- Jet-Engines Revised Dictionary for the 6th-Generation-R&D in a New Era
- Original Research Articles
- Off-Design Analysis of Transonic Bypass Fan Systems Using Streamline Curvature Through-Flow Method
- Predicting Lean Blowout and Emissions of Aircraft Engine Combustion Chamber Based on CRN
- Dielectric Barrier Discharge (DBD) Plasma Actuators for Flow Control in Turbine Engines: Simulation of Flight Conditions in the Laboratory by Density Matching
- Application of the Proper Orthogonal Decomposition Method in Analyzing Active Separation Control With Periodic Vibration Wall
- Model Predictive Control and Controller Parameter Optimisation of Combustion Instabilities
- Quasi-One-Dimensional Modeling and Analysis of RBCC Dual-Mode Scramjet Engine
- Investigation on the Performance of Forward Bending Fan
Articles in the same Issue
- Frontmatter
- Editorial
- Jet-Engines Revised Dictionary for the 6th-Generation-R&D in a New Era
- Original Research Articles
- Off-Design Analysis of Transonic Bypass Fan Systems Using Streamline Curvature Through-Flow Method
- Predicting Lean Blowout and Emissions of Aircraft Engine Combustion Chamber Based on CRN
- Dielectric Barrier Discharge (DBD) Plasma Actuators for Flow Control in Turbine Engines: Simulation of Flight Conditions in the Laboratory by Density Matching
- Application of the Proper Orthogonal Decomposition Method in Analyzing Active Separation Control With Periodic Vibration Wall
- Model Predictive Control and Controller Parameter Optimisation of Combustion Instabilities
- Quasi-One-Dimensional Modeling and Analysis of RBCC Dual-Mode Scramjet Engine
- Investigation on the Performance of Forward Bending Fan
