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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)
Date Acquired
August 15, 2013
Publication Date
July 1, 1992
Subject Category
Fluid Mechanics And Heat Transfer
Report/Patent Number
AIAA PAPER 92-3763
Accession Number
92A54153
Funding Number(s)
CONTRACT_GRANT: NAS8-38609
Distribution Limits
Public
Copyright
Other

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