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Investigation of the boiling characteristics of liquid oxygen flow in a liquid rocket engine.

Author(s) : CHO N. K., JEONG S. K.

Summary

In most cryogenic liquid rocket engines, liquid oxygen manifold and injector are not thermally insulated from room temperature environment for reducing system complexity and the weight. This feature of cryogenic liquid rocket engine results in the situation that liquid oxygen flow is easy to be vaporized especially in the vicinity of the manifold and the injector wall. The research in the paper is focused on two-phase flow phenomena of liquid oxygen in rocket engine. Vapour fraction is estimated by comparing the measured two-phase flow pressure drop in the engine manifold and the injector with the ideal single-phase pressure drop. Heat flux into cryogenic flow is estimated by measuring the wall temperature on the engine manifold to examine boiling characteristics. Suitable correlations for cryogenic two-phase flow are reviewed to examine their applicability. Additionally, the effect of vapour generation in liquid rocket engine manifold and injector on engine performance and combustion suitability is considered.

Details

  • Original title: Investigation of the boiling characteristics of liquid oxygen flow in a liquid rocket engine.
  • Record ID : 2006-1070
  • Languages: English
  • Source: Cryogenics and refrigeration. Proceedings of ICCR 2003.
  • Publication date: 2003/04/22

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