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Investigation of helium injection cooling to liquid oxygen propellant chamber.

Author(s) : CHO N. K., KWON O. S., KIM Y., et al.

Summary

Subcooling of cryogenic propellant by helium injection is one of the most effective methods for suppressing bulk boiling and keeping subcooled liquid oxygen before rocket launch. In order to design the cooling system, understanding of the limitations of heat and mass transfer is required. In this paper, an analytical model for the helium injection system is presented. This model's main feature is the representation of bubbling system using finite-rate heat transfer and instantaneous mass transfer concept. With this simplified approach, the effect of helium injection to liquid oxygen system under several circumstances is examined. Experimental results along with simulations of single bubble rising in liquid oxygen and bubbling system are presented with various helium injection flow rates, helium temperatures, and injection methods. The overall cooling effect for rocket application is also discussed. [Reprinted with permission from Elsevier. Copyright, 2005].

Details

  • Original title: Investigation of helium injection cooling to liquid oxygen propellant chamber.
  • Record ID : 2006-2798
  • Languages: English
  • Publication date: 2006/02
  • Source: Source: Cryogenics/Proc. Space Cryog. Workshop, Colorado Springs
    vol. 46; n. 2-3; 132-142; fig.; tabl.; 19 ref.

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