Rocket Engine Combustion Chamber Equations

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SUMMARY

This discussion focuses on the equations and design considerations for rocket engine combustion chambers and De Laval nozzles. Key insights include the use of NASA's RAMP program for nozzle analysis and the specific design parameters of the Space Shuttle Main Engine (SSME), which features an area ratio of 69:1, a chamber pressure of 2,994 psia, and a mixture ratio of 6.0. The SSME dimensions are specified as 168 inches in length and 96 inches in diameter, emphasizing the relationship between chamber dimensions and nozzle design.

PREREQUISITES
  • Understanding of rocket propulsion principles
  • Familiarity with combustion chamber design
  • Knowledge of De Laval nozzle theory
  • Basic proficiency in fluid dynamics
NEXT STEPS
  • Research the RAMP program used by NASA for nozzle design analysis
  • Study the design equations for rocket combustion chambers
  • Examine AIAA publications on propulsion and combustion chamber design
  • Explore the specific design parameters of the Space Shuttle Main Engine (SSME)
USEFUL FOR

Aerospace engineers, propulsion specialists, and students studying rocket engine design will benefit from this discussion, particularly those focused on combustion chamber and nozzle design principles.

FiggyOO
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Good evening all,

I was wondering if anyone would be able to point me in the right direction to equations in regards to designing a proper combustion chamber for a rocket engine, as well as for the throat/De Laval nozzle as well. I've looked around and I can't seem to find anything that covers the actual dimensions of the chamber.
 
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I don't think things are just as easy as using equations & feeding numbers for designing purpose.
 
This might be useful.

http://www.pwrengineering.com/articles/nozzledesign.htm


NASA Marshall used a program called RAMP to analyze nozzle designs. I would expect Rocketdyne (now part of United Technologies/Pratt & Whitney) used their own proprietary code.

Search Google or other search engine with "SSME","nozzle"

The SSME uses an H2-rich mixture.

AIAA has a number of books on propulsion, including some description of combustion chambers, throats, and nozzles.
 
Last edited by a moderator:
Thanks, I know there are equations to make a proper combustion chamber though. I know that the chamber needs to be a certain length and diameter in relation to the nozzle.
 
One could take a cross-section and simply plot diameter or radius of nozzle as a function of distance from throat.

For SSME -
Area Ratio: 69:1
Chamber Pressure: 2,994 psia
Engine Mixture Ratio: 6.0 (IIRC, mass O2/mass H2)

Dimensions
Length: 168 in.
Diameter: 96 in.

http://www.enginehistory.org/SSME/SSME1.pdf
 
Last edited by a moderator:

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