The effect of various parameters on the energy losses in the combustion chambers of oxygen/hydrogen, fluorine/hydrogen, and fluorine/ ammonia rocket engines was investigated. A thrust variation of the capacitatively cooled experimental rocket engines between 200 N and 1,500 N was provided by a combustion chamber pressure variation between 3 bars and 15 bars. The energy losses of a fluorine/ammonia rocket engine were compared with results obtained with the Distribution Energy Release computer model. The results of the investigation are presented as two-dimensional approximation functions. The energy losses of rocket engines with coaxial injectors can be described by the two parameters MIXEFF and VAPTIME, which characterize the imperfect mixing and the incomplete vaporization of the propellants.
Energy Losses in High Energy Rocket Engines with Thrust Variation
1977
102 pages
Report
Keine Angabe
Englisch
Variable Thrust Rocket Engines
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