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.
All Science Journal Classification (ASJC) codes
- Aerospace Engineering
- Fuel Technology
- Mechanical Engineering
- Space and Planetary Science