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 journalArticle

11 Citations (Scopus)

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 - Jan 1 2002

Fingerprint

liquid oxygen
atomizing
Atomization
injectors
momentum
Momentum
shear
preburners
liquid
droplet
Space Shuttle Main Engine
Liquids
pressure chambers
space shuttle
Space shuttles
combustion chambers
liquids
Combustion chambers
Rockets
rockets

All Science Journal Classification (ASJC) codes

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

Cite this

Ferraro, M. ; Kujala, R. J. ; Thomas, J. L. ; Glogowski, M. J. ; Micci, M. M. / Effects of GH2/LOX velocity and momentum ratios on shear coaxial injector atomization. In: Journal of Propulsion and Power. 2002 ; Vol. 18, No. 1. pp. 209-211.
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Effects of GH2/LOX velocity and momentum ratios on shear coaxial injector atomization. / Ferraro, M.; Kujala, R. J.; Thomas, J. L.; Glogowski, M. J.; Micci, M. M.

In: Journal of Propulsion and Power, Vol. 18, No. 1, 01.01.2002, p. 209-211.

Research output: Contribution to journalArticle

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