Prediction of high frequency combustion instability in liquid propellant rocket enginesThe present use of a numerical model developed for the prediction of high-frequency combustion stabilities in liquid propellant rocket engines focuses on (1) the overall behavior of nonlinear combustion instabilities (2) the effects of acoustic oscillations on the fuel-droplet vaporization and combustion process in stable and unstable engine operating conditions, oscillating flowfields, and liquid-fuel trajectories during combustion instability, and (3) the effects of such design parameters as inlet boundary conditions, initial spray conditions, and baffle length. The numerical model has yielded predictions of the tangential-mode combustion instability; baffle length and droplet size variations are noted to have significant effects on engine stability.
Document ID
19920071529
Acquisition Source
Legacy CDMS
Document Type
Conference Paper
Authors
Kim, Y. M. (NASA Marshall Space Flight Center Huntsville, AL, United States)
Chen, C. P. (NASA Marshall Space Flight Center Huntsville, AL, United States)
Ziebarth, J. P. (Alabama, University Huntsville, United States)
Chen, Y. S. (Engineering Science, Inc. Huntsville, AL, United States)