International Journal of Aerospace System Engineering

The Society for Aerospace System Engineering (항공우주시스템공학회)
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System Analysis of a Gas Generator Cycle Rocket Engine

  • Cho, Won Kook (Rocket Engine Team, Korea Aerospace Research Institute) ;
  • Kim, Chun IL (Department of Mechanical Engineering, University of Alberta)
  • Received : 2018.06.27
  • Accepted : 2019.10.15
  • Published : 2019.12.31
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Abstract

A system analysis program has been developed for a gas generator cycle liquid rocket engine of 30 ton class. Numerical models have been proposed for a combustor, a turbopump, a gas generator and pressure drop through a regenerative cooling system. Numerical algorithm has been validated by comparing with the published data of MC-1. The major source of error is not the numerical algorithm but the imperfect performance models of subsystems. So the precision of the program can be improved by revising the performance models using experimental data. The sea level specific impulse and vacuum specific impulse have been demonstrated for a 30 ton class gas generator engine. The optimal condition of combustor pressure and mixture ratio for specific impulse which is a typical characteristic of a gas generator cycle engine has been illustrated.

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References

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