THERMAT is a Python-based tool designed to analyze heat transport in rocket engine combustion chambers and to support the design of regenerative cooling systems.
It uses Cantera for chemical equilibrium and flow calculations, and CoolProp for accurate fluid property data.
thermat/
├── main.py # Entry point: runs thermal analysis
├── core/
│ ├── therm_functions.py # Main functions for geometry, flow, and thermal analysi
├── utilities/ # Additional scripts not required for the core functionality
├── README.md
├── requirements.txt
git clone https://github.com/flxbrt/thermat.git
cd thermatpip install -r requirements.txtpython main.pyThis tool will
- Generate chamber and cooling channel geometry
- Solve flow properties 1D (axially discretized) based on isentropic flow along the combustion chamber; as of now the flow is computed for frozen conditions only; equilibirum flow will be implemented at a leter point
- Perform a thermal analysis and compute heat fluxes and temperatures (either fixed wall or regenerative cooling)
- Output plots and performance metrics such as absorbed heat and coolant heat capacity
- Allows fixed wall temperature or full regenerative cooling analysis with variable cooling geometry and number of channels
- Automatically detects infeasible cooling geometries
- Suports different propellant combinations
- Supports frozen flow / chemistry
- The hot gas side heat transfer is validated against the subscale SSME engine
- Equilibrium flow / chemistry
- Provide calibration data on a 3kN liquid ethanol cryogenic oxygen engine once test campaigns has been conducted
Developed by @flxbrt Version: 2.0