- The code stems from the minimization of the free energy of the system by using Lagrange multipliers combined with a Newton-Raphson method, upon condition that initial gas properties are defined by two functions of states (e.g., temperature and pressure)
- When temperature is not externally imposed, the code retrieves a routine also based on Newton-Raphson method to find the equilibrium temperature
- Solve processes that involve strong changes in the dynamic pressure, such as detonations and shock waves in the steady state
- Find the equilibrium conditions of the different phenomena undergoing behind the shock: molecular vibrational excitation up to dissociation, and electronic excitation up to ionization, thereby providing the
properties of the gas in plasma statewithin the temperature range given by the NASA’s 9-coefficient polynomial fits. - Calculate the chemical equilibrium composition of a mixture by selecting which species can react or remain chemically frozen (inert).
- The corresponding thermodynamic properties of the species are modelled with
NASA’s 9-coefficient polynomial fits, which rangesup to 20000 K, and the ideal gas equation of state - Results are in
excellent agreement with NASA’s Chemical Equilibrium with Applications (CEA) program, CANTERA and Caltech’s Shock and Detonation Toolbox, and TEA
Chemical equilibrium problems- TP: Equilibrium composition at defined temperature and pressure
- HP: Adiabatic temperature and composition at constant pressure
- SP: Isentropic compression/expansion to a specified pressure
- TV: Equilibrium composition at defined temperature and constant volume
- EV: Adiabatic temperature and composition at constant volume
- SV: Isentropic compression/expansion to a specified volume
Shock calculations:- Pre-shock and post-shock states
- Equilibrium or frozen composition
- Incident or reflected shocks
- Chapman-Jouguet detonations, overdriven detonations, and underdriven detonations
- Reflected detonations
- Oblique shocks/detonations
- Shock/detonation polar curves for incident and reflected states
- Hugoniot curves
- Ideal jump conditions for a given adiabatic index and pre-shock Mach number
Rocket propellant performance assuming:- Infinite-Area-Chamber model (IAC)
- Finite-Area-Chamber model (FAC)
- All the routines and computations are encapsulated in a more comprehensive and
user-friendly GUI - The code
is in it’s transition to Python - Export results in a spreadsheet
- Export results as a .mat format
Display predefined plots(e.g., molar fraction vs. equilence ratio)
This project is also part of the PhD of Alberto Cuadra-Lara.
- The tutorials will help you get started using the Combustion Toolbox on your pc.
- See examples of Combustion Toolbox applications.
- Check the documentation of almost every functions.
We have several examples of what the Combustion Toolbox can do. Here we show a preview of the GUI and some results obtained from the Combustion Toolbox.
Figure 1: Current state of the GUI.
Figure 2: Hugoniot curves for different molecular gases at pre-shock temperature T1 = 300 K and pressure p1 = 1 atm [numerical results obtained with Combustion Toolbox (lines) and contrasted with NASA’s Chemical Equilibrium with Applications (CEA) code excluding ionization (symbols)].
Figure 3: Example CJ detonation for lean to rich CH4-air mixtures at standard conditions: (a) variation of molar fraction, (b) variation of temperature. The computational time was of 9.25 seconds using a Intel(R) Core(TM) i7-8700 CPU @ 3.20GHz for a set of 24 species considered and a total of 351 case studies.
Figure 4: Pressure-deflection shock polar (left) and wave angle-deflection shock polar (right) for an air mixture (78.084% N2, 20.9476% O2, 0.9365% Ar, 0.0319% CO2) at pre-shock temperature T1 = 300 K and pressure p1 = 1 atm, and a range of preshock Mach numbers M1 = [2, 14]; line: considering dissociation, ionization, and recombination in multi-species mixtures; dashed: considering a thermochemically frozen air mixture.
Please read CONTRIBUTING.md for details of the process for submitting pull requests to the repository.
Please send feedback or inquiries to [email protected]
Thank you for using the Combustion Toolbox!
- Combustion Toolbox's color palette is obtained from the following repository: Stephen (2021). ColorBrewer: Attractive and Distinctive Colormaps (https://github.com/DrosteEffect/BrewerMap), GitHub. Retrieved December 3, 2021.
- For validations, Combustion Toolbox uses CPU Info from the following repository: Ben Tordoff (2022). CPU Info (https://github.com/BJTor/CPUInfo/releases/tag/v1.3), GitHub. Retrieved March 22, 2022.
- Combustion Toolbox's splash screen is based on a routine from the following repository: Ben Tordoff (2022). SplashScreen (https://www.mathworks.com/matlabcentral/fileexchange/30508-splashscreen), MATLAB Central File Exchange. Retrieved October 15, 2022.
- Combustion Toolbox's periodic table layout is based in the following repository: Bruno Salcedo (2018). latex-periodic-table (https://github.com/brunosalcedo/latex-periodic-table), Github. Retrieved October 15, 2022.
- Alberto Cuadra-Lara - Lead developer
- César Huete - Advisor
- Marcos Vera - Advisor
Grupo de Mecánica de Fluidos, Universidad Carlos III, Av. Universidad 30, 28911, Leganés, Spain
See also the list of contributors who participated in this project.
@misc{combustiontoolbox,
author = "Cuadra, A. and Huete, C. and Vera, M.",
title = "Combustion Toolbox: A MATLAB-GUI based open-source tool for solving gaseous combustion problems",
year = 2024,
note = "Version 1.0.5",
doi = {https://doi.org/10.5281/zenodo.5554911}
}
@phdthesis{cuadra2023_thesis,
title = {Development of a wide-spectrum thermochemical code with application to planar reacting and non-reacting shocks},
author = {Cuadra, A.},
year = 2023,
month = {May},
address = {Madrid, Spain},
note = {Available at \url{http://hdl.handle.net/10016/38179}},
school = {Universidad Carlos III de Madrid},
type = {PhD thesis}
}
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