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

doi:10.2514/2.5920

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 journal › Article › peer-review

16 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 language	English (US)
Pages (from-to)	209-211
Number of pages	3
Journal	Journal of Propulsion and Power
Volume	18
Issue number	1
DOIs	https://doi.org/10.2514/2.5920
State	Published - 2002

All Science Journal Classification (ASJC) codes

Aerospace Engineering
Fuel Technology
Mechanical Engineering
Space and Planetary Science

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10.2514/2.5920

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title = "Effects of GH2/LOX velocity and momentum ratios on shear coaxial injector atomization",

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.",

author = "M. Ferraro and Kujala, \{R. J.\} and Thomas, \{J. L.\} and Glogowski, \{M. J.\} and Micci, \{M. M.\}",

year = "2002",

doi = "10.2514/2.5920",

language = "English (US)",

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pages = "209--211",

journal = "Journal of Propulsion and Power",

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publisher = "American Institute of Aeronautics and Astronautics Inc. (AIAA)",

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AU - Ferraro, M.

AU - Kujala, R. J.

AU - Thomas, J. L.

AU - Glogowski, M. J.

AU - Micci, M. M.

PY - 2002

Y1 - 2002

N2 - 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.

AB - 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.

UR - https://www.scopus.com/pages/publications/0036158379

UR - https://www.scopus.com/pages/publications/0036158379#tab=citedBy

U2 - 10.2514/2.5920

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AN - SCOPUS:0036158379

SN - 0748-4658

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SP - 209

EP - 211

JO - Journal of Propulsion and Power

JF - Journal of Propulsion and Power

IS - 1

ER -

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

Abstract

All Science Journal Classification (ASJC) codes

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