Accession Number : ADA329605
Title : Nonlinear, Rotational-Acoustic Processes in Solid Rocket Engines
Descriptive Note : Final technical rept. 1 Jan 94-30 Apr 97
Corporate Author : COLORADO UNIV AT BOULDER DEPT OF MECHANICAL ENGINEERING
Personal Author(s) : Kassoy, D. R.
PDF Url : ADA329605
Report Date : 30 JUN 1997
Pagination or Media Count : 197
Abstract : Solid rocket motor chamber fluid dynamics are modeled using the full Navier Stokes equations. Mass injection from the sidewall of a cylinder simulates the propellant gasification. Prescribed boundary disturbances in velocity or pressure induce acoustic waves and other transients into the chamber geometry. Vorticity is generated on the sidewall from an inviscid interaction between transient pressure gradients and the fluid injected from the surface. Axisymmetric and three dimensional solutions obtained from analysis and computation are used to predict the dynamics of the co existing acoustic and rotational flows. Results suggest that intense transient vorticity is present throughout much of the chamber during a firing as long as acoustic transients are present. The rotational flow component is associated with intense transient shear stresses on the sidewall. Meanflow profiles and RMS intensity distributions are similar to those found in traditional turbulent pipe flows with injection. Traditional acoustic stability theory, based on purely irrotational flow assumptions, may describe the pressure variations in chamber models, but cannot describe the rotational component of the flow found in the present model.
Descriptors : *GAS DYNAMICS, *SOLID PROPELLANT ROCKET ENGINES, PRESSURE GRADIENTS, ACOUSTIC WAVES, TURBULENT FLOW, THREE DIMENSIONAL, SHEAR STRESSES, AXISYMMETRIC, NAVIER STOKES EQUATIONS, INVISCID FLOW.
Subject Categories : Solid Propellant Rocket Engines
Distribution Statement : APPROVED FOR PUBLIC RELEASE