Source code for RCAIDE.Library.Attributes.Propellants.Jet_A
# RCAIDE/Library/Attributes/Propellants/Jet_A.py
#
#
# Created: Mar 2024, M. Clarke
# ----------------------------------------------------------------------------------------------------------------------
# Imports
# ----------------------------------------------------------------------------------------------------------------------
from .Propellant import Propellant
from RCAIDE.Framework.Core import Data
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# Jet_A1 Propellant Class
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[docs]
class Jet_A(Propellant):
"""
A class representing Jet A aviation kerosene fuel properties and emissions characteristics.
Attributes
----------
tag : str
Identifier for the propellant ('Jet_A')
reactant : str
Oxidizer used for combustion ('O2')
density : float
Fuel density in kg/m³ (820.0)
specific_energy : float
Specific energy content in J/kg (43.02e6)
energy_density : float
Energy density in J/m³ (35276.4e6)
lower_heating_value : float
Lower heating value in J/kg (43.24e6)
max_mass_fraction : Data
Maximum fuel-to-oxidizer mass ratios
- Air : float
Maximum mass fraction with air (0.0633)
- O2 : float
Maximum mass fraction with pure oxygen (0.3022)
use_high_fidelity_kinetics_model : bool
Flag for using detailed chemical kinetics (True)
fuel_surrogate_chemical_properties : dict
Simplified surrogate composition
- N-C12H26 : float
Dodecane fraction (0.6)
- A1CH3 : float
Toluene fraction (0.2)
- A1 : float
Benzene fraction (0.2)
fuel_chemical_properties : dict
Detailed chemical composition for high-fidelity model
emission_indices : Data
Emission indices in kg/kg fuel
- Production : float
CO2 production rate (0.4656)
- CO2 : float
Carbon dioxide (3.16)
- CO : float
Carbon monoxide (0.00201)
- H2O : float
Water vapor (1.34)
- SO2 : float
Sulfur dioxide (0.0012)
- NOx : float
Nitrogen oxides (0.01514)
- Soot : float
Particulate matter (0.0012)
global_warming_potential_100 : Data
100-year global warming potentials
- CO2 : float
Carbon dioxide (1)
- H2O : float
Water vapor (0.06)
- SO2 : float
Sulfur dioxide (-226)
- NOx : float
Nitrogen oxides (52)
- Soot : float
Particulate matter (1166)
- Contrails : float
Contrail formation (11)
Notes
-----
This class implements properties for Jet A aviation kerosene, including both
simplified and detailed chemical kinetics options. Properties are specified at
standard conditions (15°C, 1 atm).
**Definitions**
'Emission Index'
Mass of pollutant produced per mass of fuel burned
'Global Warming Potential'
Relative measure of heat trapped in atmosphere compared to CO2
'Surrogate Model'
Simplified three-component representation of complex fuel mixture
**Major Assumptions**
* Properties are for standard temperature and pressure conditions (15C, 1atm)
* Surrogate model uses three-component representation
* Detailed model includes complex hydrocarbon mixture
* Emission indices are for typical aircraft cruise conditions
References
----------
[1] D.S. Lee, D.W. Fahey, A. Skowron, M.R. Allen, U. Burkhardt, Q. Chen, S.J. Doherty, S. Freeman, P.M. Forster, J. Fuglestvedt, A. Gettelman, R.R. De León, L.L. Lim, M.T. Lund, R.J. Millar, B. Owen, J.E. Penner, G. Pitari, M.J. Prather, R. Sausen, L.J. Wilcox, "The contribution of global aviation to anthropogenic climate forcing for 2000 to 2018," Atmospheric Environment, Volume 244, 2021, 117834, ISSN 1352-2310, https://doi.org/10.1016/j.atmosenv.2020.117834.
[2] Chevron Products Company. (n.d.). Aviation fuels. Chevron. https://www.chevron.com/-/media/chevron/operations/documents/aviation-tech-review.pdf
"""
def __defaults__(self):
"""This sets the default values.
Assumptions:
None
Source:
Emission Indices from Lee, David S., et al. "The contribution of global aviation to anthropogenic climate forcing
for 2000 to 2018." Atmospheric environment 244 (2021): 117834
"""
self.tag = 'Jet_A'
self.reactant = 'O2'
self.density = 820.0 # kg/m^3 (15 C, 1 atm)
self.specific_energy = 43.02e6 # J/kg
self.energy_density = 35276.4e6 # J/m^3
self.lower_heating_value = 43.24e6 # J/kg
self.heat_of_vaporization = 300000 # J/kg
self.stoichiometric_fuel_air_ratio = 0.068
self.max_mass_fraction = Data({'Air' : 0.0633,'O2' : 0.3022}) # kg propellant / kg oxidizer
self.stoichiometric_fuel_air_ratio = 0 # [-] Stoichiometric Fuel to Air ratio
self.heat_of_vaporization = 0 # [J/kg] Heat of vaporization at standard conditions
self.temperature = 0 # [K] Temperature of fuel
self.pressure = 0 # [Pa] Pressure of fuel
self.fuel_surrogate_S1 = {} # [-] Mole fractions of fuel surrogate species
self.kinetic_mechanism = '' # [-] Kinetic mechanism for fuel surrogate species
self.oxidizer = ''
# critical temperatures
self.temperatures.flash = 311.15 # K
self.temperatures.autoignition = 483.15 # K
self.temperatures.freeze = 233.15 # K
self.temperatures.boiling = 0.0 # K
self.emission_indices.Production = 0.4656 # kg/kg Greet
self.emission_indices.CO2 = 3.16 # kg/kg
self.emission_indices.CO = 0.00201 # kg/kg
self.emission_indices.H2O = 1.23 # kg/kg
self.emission_indices.SO2 = 0.0012 # kg/kg
self.emission_indices.NOx = 0.01514 # kg/kg
self.emission_indices.Soot = 0.0012 # kg/kg
self.global_warming_potential_100.CO2 = 1 # CO2e/kg
self.global_warming_potential_100.H2O = 0.06 # CO2e/kg
self.global_warming_potential_100.SO2 = -226 # CO2e/kg
self.global_warming_potential_100.NOx = 52 # CO2e/kg
self.global_warming_potential_100.Soot = 1166 # CO2e/kg
self.global_warming_potential_100.Contrails = 11 # kg/CO2e/km
