Source code for RCAIDE.Library.Attributes.Propellants.Jet_A1
# RCAIDE/Library/Attributes/Propellants/Jet_A1.py
#
#
# Created: Mar 2024, M. Clarke
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# 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_A1(Propellant):
"""
A class representing Jet A-1 aviation kerosene fuel properties and emissions characteristics.
Similar to Jet A but with a lower freezing point for international operations.
Attributes
----------
tag : str
Identifier for the propellant ('Jet_A1')
reactant : str
Oxidizer used for combustion ('O2')
density : float
Fuel density in kg/m³ (804.0)
specific_energy : float
Specific energy content in J/kg (43.15e6)
energy_density : float
Energy density in J/m³ (34692.6e6)
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)
temperatures : Data
Critical temperatures in K
- flash : float
Flash point (311.15)
- autoignition : float
Autoignition temperature (483.15)
- freeze : float
Freezing point (226.15)
- boiling : float
Boiling point (0.0)
emission_indices : Data
Emission indices in kg/kg fuel
- Production : float
CO2 production rate (0.4656)
- CO2 : float
Carbon dioxide (3.16)
- 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-1 aviation kerosene, the international
variant of Jet A with enhanced cold-weather performance. Properties are specified
at standard conditions (15°C, 1 atm).
**Definitions**
'Flash Point'
Lowest temperature at which fuel vapors will ignite
'Autoignition Temperature'
Temperature at which fuel will ignite without external ignition source
'Freeze Point'
Temperature at which fuel begins to form solid crystals
**Major Assumptions**
* Properties are for standard temperature and pressure conditions
* Surrogate model uses three-component representation
* Detailed model includes complex hydrocarbon mixture
* Emission indices are for typical aircraft cruise conditions
References
----------
[1] Randall C. Boehm, Zhibin Yang, David C. Bell, John Feldhausen, Joshua S. Heyne, "Lower heating value of jet fuel from hydrocarbon class concentration data and thermo-chemical reference data: An uncertainty quantification," Fuel, Volume 311, 2022, 122542, ISSN 0016-2361, https://doi.org/10.1016/j.fuel.2021.122542.
[2] NASA's Engine Performance Program (NEPP)
"""
def __defaults__(self):
"""This sets the default values.
Assumptions:
None
Source:
lower_heating_value: Boehm et al, Lower Heating Value of Jet Fuel From Hydrocarbon Class Concentration Data
and Thermo-Chemical Reference Data: An Uncertainty Quantification
emission indices: NASA's Engine Performance Program (NEPP) and
"""
self.tag = 'Jet A1'
self.reactant = 'O2'
self.density = 804.0 # kg/m^3 (15 C, 1 atm)
self.specific_energy = 43.15e6 # J/kg
self.energy_density = 34692.6e6 # J/m^3
self.lower_heating_value = 43.24e6 # J/kg
self.max_mass_fraction = Data({'Air' : 0.0633, 'O2' : 0.3022}) # kg propellant / kg oxidizer
self.temperatures.flash = 311.15 # K
self.temperatures.autoignition = 483.15 # K
self.temperatures.freeze = 226.15 # K
self.temperatures.boiling = 0.0 # K
self.stoichiometric_fuel_air_ratio = 0.068 # [-] Stoichiometric Fuel to Air ratio
self.heat_of_vaporization = 360000 # [J/kg] Heat of vaporization at standard conditions
self.temperature = 298.15 # [K] Temperature of fuel
self.pressure = 101325 # [Pa] Pressure of fuel
self.fuel_surrogate_S1 = {'NC12H26':0.404, 'IC8H18':0.295, 'TMBENZ' : 0.073,'NPBENZ':0.228, 'C10H8':0.02} # [-] Mole fractions of fuel surrogate species
self.kinetic_mechanism = 'Fuel.yaml' # [-] Kinetic mechanism for fuel surrogate species
self.oxidizer = 'Air.yaml'
# 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 fuel
self.emission_indices.H2O = 1.23 # kg/kg fuel
self.emission_indices.SO2 = 0.0012 # kg/kg fuel
self.emission_indices.NOx = 0.01514 # kg/kg fuel
self.emission_indices.Soot = 0.0012 # kg/kg fuel
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
