Premium
Shear layer instability and acoustic interaction in solid propellant rocket motors
Author(s) -
Kourta A.
Publication year - 1997
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/(sici)1097-0363(19971030)25:8<973::aid-fld599>3.0.co;2-d
Subject(s) - solid fuel rocket , propellant , instability , mechanics , aeroacoustics , rocket (weapon) , thrust , vortex , physics , materials science , inviscid flow , rocket engine , aerospace engineering , acoustics , sound pressure , engineering
Segmentation of solid propellant rocket motors has been demonstrated to be a source of unpredicted and undesirable pressure and thrust oscillations. Surface discontinuities are the primary cause of these vortex‐shedding‐driven oscillations, which result from a strong coupling between the shear layer instability and the acoustic motion in the chamber. The analysis of an axisymmetric geometry corresponding to a {1\over 15} subscale P230 motor of the Ariane 5 rocket is numerically computed. With a suitable mesh for the viscosity value studied, the aeroacoustics in the chamber is fully described. A coupling between the hydrodynamic instability and the organ‐pipe acoustic mode is clearly demonstrated. The mechanism for frequency selection is discussed. © 1997 John Wiley & Sons, Ltd.