https://github.com/wyllduck/rocket_combustion_chamber_optimizer

https://github.com/wyllduck/rocket_combustion_chamber_optimizer

Last synced: 3 days ago
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• Host: GitHub
• URL: https://github.com/wyllduck/rocket_combustion_chamber_optimizer
• Owner: WyllDuck
• Created: 2023-03-02T20:16:49.000Z (almost 2 years ago)
• Default Branch: main
• Last Pushed: 2023-03-27T13:22:38.000Z (almost 2 years ago)
• Last Synced: 2024-11-10T00:44:41.560Z (2 months ago)
• Language: Python
• Size: 11.7 MB
• Stars: 1
• Watchers: 1
• Forks: 0
• Open Issues: 0
• Metadata Files:
  • Readme: README.md

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README

        
# rocket_combustion_chamber_optimizer

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

# Explanaition

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?