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 | |
| State | Published - Jan 1 2002 |
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All Science Journal Classification (ASJC) codes
- Aerospace Engineering
- Fuel Technology
- Mechanical Engineering
- Space and Planetary Science
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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 journal › Article
TY - JOUR
T1 - Effects of GH2/LOX velocity and momentum ratios on shear coaxial injector atomization
AU - Ferraro, M.
AU - Kujala, R. J.
AU - Thomas, J. L.
AU - Glogowski, M. J.
AU - Micci, M. M.
PY - 2002/1/1
Y1 - 2002/1/1
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 - http://www.scopus.com/inward/record.url?scp=0036158379&partnerID=8YFLogxK
UR - http://www.scopus.com/inward/citedby.url?scp=0036158379&partnerID=8YFLogxK
U2 - 10.2514/2.5920
DO - 10.2514/2.5920
M3 - Article
AN - SCOPUS:0036158379
VL - 18
SP - 209
EP - 211
JO - Journal of Propulsion and Power
JF - Journal of Propulsion and Power
SN - 0748-4658
IS - 1
ER -