Rocket Engine Combustion Chamber Equations

  • Thread starter FiggyOO
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  • #1
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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.
 

Answers and Replies

  • #2
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I don't think things are just as easy as using equations & feeding numbers for designing purpose.
 
  • #3
Astronuc
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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.
 
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  • #4
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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.
 
  • #5
Astronuc
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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
 
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