Effects of GH2/LOX velocity and momentum ratios on shear coaxial injector atomization

M. Ferraro, R. J. Kujala, J. L. Thomas, M. J. Glogowski, M. M. Micci

Research output: Contribution to journalArticlepeer-review

12 Scopus citations

Abstract

The effects of GH2/LOX velocity and momentum ratios on shear coaxial injector atomization were analyzed. A subscale rocket combustion chamber was operated with a single full-size Space Shuttle Main Engine (SSME) preburner element at a liquid oxygen flow rate of 0.113 kg/s. A correlation was presented to predict the droplet arithmetic mean diameter as a function of gas/liquid momentum ratio for chamber pressures between 2.0 and 4.5 MPa. Results indicated a decrease in LOX droplet sizes with increasing gas/liquid velocity or momentum ratio.

Original languageEnglish (US)
Pages (from-to)209-211
Number of pages3
JournalJournal of Propulsion and Power
Volume18
Issue number1
DOIs
StatePublished - 2002

All Science Journal Classification (ASJC) codes

  • Aerospace Engineering
  • Fuel Technology
  • Mechanical Engineering
  • Space and Planetary Science

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