Calculation of the dimensions of the regenerative cooled combustion chanmber of a rocket engine Assumptions:
- Methane coolant at supercritical pressure (change of phase does not requiere an extra heat transfer)
- Cooled from the throat of the engine to the injection plate
This code discritizes the combustion chamber in N section (~20) and solves the temperature at the combustion chamber wall (T_wi), the coolant channel wall (T_wo) and the coolants temepratures (T_in, T_out). The concept to solve this system was proven in an excel sheet for 1 section and now I want to scale it up to get the final design parameters.
The final objective is to determine the temperature along the CC walls to find a feasible design for the CC.
Questions:
- I have the combustion temperature of the hot gas (inside the combustion chamber) and the inner diameter of the CC (Di) for every section (Di: f(x)). With this information I want to obtain the temperature at every position of the CC (T:f(x)) (inside the thrust chamber and the nozzle) based on the Di using something similar to the ideal gas law. Could that work? Which function is that one?