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Pressure‐based method for combustion instability analysis
Author(s) -
Kim Y. M.,
Chen Z. J.,
Chen C. P.,
Ziebarth J. P.
Publication year - 1994
Publication title -
international journal for numerical methods in fluids
Language(s) - English
Resource type - Journals
SCImago Journal Rank - 0.938
H-Index - 112
eISSN - 1097-0363
pISSN - 0271-2091
DOI - 10.1002/fld.1650191103
Subject(s) - combustion , mechanics , instability , combustor , shock tube , rocket (weapon) , transient (computer programming) , vaporization , liquid propellant rocket , flow (mathematics) , ramjet , combustion chamber , materials science , aerospace engineering , physics , shock wave , engineering , thermodynamics , computer science , chemistry , propellant , organic chemistry , operating system
An improved pressure‐based method has been applied to predict the two‐dimensional instability analysis of liquid‐fuelled rocket engines. This method is non‐iterative for transient flow calculations and applicable to all‐speed flows. Validation cases include the shock‐tube problem, the blast flow field and unsteady spraycombusting flows. Computations for the combustion instability analysis were carried out for various combustion parameters such as spray initial conditions and combustor geometries. Unsteady behaviours of the stable and unstable spray flame fields and effects of acoustic oscillations on the fuel droplet vaporization and combustion process are studied in detail. The present numerical model successfully demonstrates the capability of predicting combustion instability as well as fast transient compressible flows at all speeds.