Propellant Vaporization as a Criterion for Rocket-engine Design; Calculations of Chamber Length to Vaporize Various Propellants
Propellant Vaporization as a Criterion for Rocket-engine Design; Calculations of Chamber Length to Vaporize Various Propellants

Author: Richard J. Priem

Publisher:

Published: 1958

Total Pages: 36

ISBN-13:

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Vaporization rates were calculated for drops of n-heptane, ammonia, hydrazine, oxygen, and fluorine. The percent propellant vaporized is correlated with an effective chamber length for various spray conditions, and various engine-design and operating parameters. The results show that the effective chamber length required to vaporize a given high percentage of propellant is the shortest with oxygen and increases for fluorine, heptane, ammonia, and hydrazine in that order.

Propellant Vaporization as a Criterion for Rocket Engine Design; Calculations of Chamber Length to Vaporize a Single N-heptane Drop
Propellant Vaporization as a Criterion for Rocket Engine Design; Calculations of Chamber Length to Vaporize a Single N-heptane Drop

Author: Richard J. Priem

Publisher:

Published: 1957

Total Pages: 41

ISBN-13:

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Calculations based on droplet-evaporation theory show that for a given combustor length the percent of fuel mass vaporized can be increased by decreasing the fuel-drop size and the initial drop velocity, or by increasing chamber pressure, final gas velocity, and initial fuel temperature. The analytical results of this study were correlated to give a single curve of percent of fuel evaporated as a function of the chamber length and the factors involving these parameters. The calculated results agree with experimental results if the mass-mean-drop diameters for various injectors are assumed to be about 100 to 200 microns.