Hydrodynamic Stability Analysis of Particle-Laden Solid Rocket Motors

22nd International Conference on Spectral Line Shapes

Elliott, T.S.^1,2 ; Majdalani, J.^3

Department of Mechanical, Aerospace and Biomedical Engineering, University of Tennessee, Space Institute, Tullahoma

TN

37388, United States^1

Department of Mechanical Engineering, University of Tennessee at Chattanooga, Chattanooga

TN

37403, United States^2

Department of Aerospace Engineering, Auburn University, Auburn

AL

36849, United States^3

关键词: Destabilizing effect;    Hydrodynamic instabilities;    Hydrodynamic stability;    Linearized navier-stokes equations;    Parametric -analysis;    Pressure oscillation;    Semi-analytical solution;    Solid rocket propellant;   

Others  :  https://iopscience.iop.org/article/10.1088/1742-6596/548/1/012064/pdf
DOI  :  10.1088/1742-6596/548/1/012064

来源: IOP

【 摘 要 】

Fluid-wall interactions within solid rocket motors can result in parietal vortex shedding giving rise to hydrodynamic instabilities, or unsteady waves, that translate into pressure oscillations. The oscillations can result in vibrations observed by the rocket, rocket subsystems, or payload, which can lead to changes in flight characteristics, design failure, or other undesirable effects. For many years particles have been embedded in solid rocket propellants with the understanding that their presence increases specific impulse and suppresses fluctuations in the flowfield. This study utilizes a two dimensional framework to understand and quantify the aforementioned two-phase flowfield inside a motor case with a cylindrical grain perforation. This is accomplished through the use of linearized Navier-Stokes equations with the Stokes drag equation and application of the biglobal ansatz. Obtaining the biglobal equations for analysis requires quantification of the mean flowfield within the solid rocket motor. To that end, the extended Taylor-Culick form will be utilized to represent the gaseous phase of the mean flowfield while the self-similar form will be employed for the particle phase. Advancing the mean flowfield by quantifying the particle mass concentration with a semi-analytical solution the finalized mean flowfield is combined with the biglobal equations resulting in a system of eight partial differential equations. This system is solved using an eigensolver within the framework yielding the entire spectrum of eigenvalues, frequency and growth rate components, at once. This work will detail the parametric analysis performed to demonstrate the stabilizing and destabilizing effects of particles within solid rocket combustion.