Journal of Aerospace System Engineering (항공우주시스템공학회지)

The Society for Aerospace System Engineering (항공우주시스템공학회)
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The Effect of Partial Blockage of Flow Passage to Performance Change of a Liquid Rocket Engine

유로 단면 부분 폐쇄가 액체로켓엔진 성능 변화에 미치는 영향

  • Cho, Won Kook (Rocket Engine Dept. Korea Aerospace Research Institute)
  • 조원국 (한국항공우주연구원 발사체엔진팀)
  • Received : 2015.10.22
  • Accepted : 2015.12.01
  • Published : 2015.12.31
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Abstract

The analysis has been performed on the blockage effect at the propellant flow passage in a liquid rocket engine. This simulates an example of emergency situation where flow passage is partially blocked. The analysis method has been validated by predicting the pump head and flow rate within 1% precision against the measured data of turbopump-gas generator coupled test. When the oxidizer passage is reduced it is predicted that the mixture ratio decreases, the oxidizer pump head increases and the gas generator pressure increases. When the fuel passage is reduced it is predicted that the mixture ratio increases, fuel flow rate decreases and the fuel pump head increases.

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References

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