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Rocket injector anomalies study. Volume 2 : Results of parametric studies

Author
Singhal, A. K.
Published
Jul 1, 1984.
Physical Description
1 electronic document
Additional Creators
Tam, L. T. and Przekwas, A. J.
Online Version

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Unclassified, Unlimited, Publicly available.
Free-to-read Unrestricted online access
Summary
The employment of a existing computer program to simulate three dimensional two phase gas spray flows in liquid propellant rocket engines. This was accomplished by modification of an existing three dimensional computer program (REFLAN3D) with Euler/Lagrange approach for simulating two phase spray flow, evaporation and combustion. The modified code is referred to as REFLAN3D-SPRAY. Computational studies of the model rocket engine combustion chamber are presented. The parametric studies of the two phase flow and combustion shows qualitatively correct response for variations in geometrical and physical parameters. The injection nonuniformity test with blocked central fuel injector holes shows significant changes in the central flame core and minor influence on the wall heat transfer fluxes.
Other Subject(s)
Collection
NASA Technical Reports Server (NTRS) Collection.
Note
Document ID: 19840024359.
Accession ID: 84N32429.
NAS 1.26:174703.
NASA-CR-174703.
CHAM-H3605/16-VOL-2.
Terms of Use and Reproduction
No Copyright.
View MARC record | catkey: 15706984