Abstract
Abstract Segmented solid propellant rocket motors tend to develop unpredicted pressure and thrust oscillations that could be attributed to a periodic phenomenon. An experimental and numerical assessment of the stability of a solid propellant motor was conducted. This numerical computation was based on an experimental study carried out on a cold-flow, reduced-scale, bidimensional duct with a complex internal geometry (obstacles, outflowing cavities, submerged nozzle). The objectives of our study are to characterize the internal flow (mean, fluctuating induced by injection through a porous wall and the shear layer created at the top of the second obstacle. The code employed solves the unsteady, compressible two-dimensional (2-D) Navier-Stokes equations in a laminar regime by a predictor-corrector MacCormack scheme. Three grids are developed for the evaluation while respecting the complexity of the internal geometry. The results obtained allow us to separate the flow into two zones: one, laminar, upstream of the obstacle; the other, disturbed, downstrea, in which vortex structures develop. The phenomena of instabilities (vortex-shedding, pairing) are in accordance with the first two acoustic longitudinal modes of the chamber. Last, the numerical computations are discussed and systematically compared with the experimental results.
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