Accession Number : ADA285606


Title :   Nonlinear Acoustic Processes in a Solid Rocket Engine


Descriptive Note : Final technical rept. 30 Sep 1991-1 Jan 1994


Corporate Author : COLORADO UNIV AT BOULDER DEPT OF MECHANICAL ENGINEERING


Personal Author(s) : Kassoy, David R ; Kirkkipn, Kadir ; Zhao, Qing


Full Text : https://apps.dtic.mil/dtic/tr/fulltext/u2/a285606.pdf


Report Date : 29 Mar 1994


Pagination or Media Count : 151


Abstract : A new formulation for chamber flow dynamics in a model of solid rocket engine shows that vorticity generation and convection are prominent physical features of the flow field. Analytical and fully computational methods are employed. to describe a basically inviscid interaction between acoustic disturbances arising from specified boundary disturbances and a sidewall injected flow field which simulates propellant burning. The mathematical model, based on the Navier Stokes equations, is developed in terms of an initial value problem in order to describe the complete, natural chamber flow evolution arising from boundary driven disturbances. The approach is analogous to a direct numerical simulation, although contemporary perturbation methods are employed to extract specific spatial and temporal scales from the equations and boundary conditions. The results show that large unsteady vorticity is created at the injected surface (sidewall) and convects into the cylinder with the radial component of the injection flow velocity.


Descriptors :   *COMBUSTION , *ACOUSTICS , *SOLID PROPELLANT ROCKET ENGINES , VELOCITY , MATHEMATICAL MODELS , SIMULATION , INJECTION , INTERACTIONS , ACOUSTIC WAVES , FORMULATIONS , CONVECTION , VORTICES , BOUNDARIES , FLOW FIELDS , NONLINEAR SYSTEMS , PERTURBATIONS , UNSTEADY FLOW , NAVIER STOKES EQUATIONS , ROCKET ENGINES , CHAMBERS , BOUNDARY LAYER FLOW


Subject Categories : Acoustics
      Combustion and Ignition
      Solid Propellant Rocket Engines


Distribution Statement : APPROVED FOR PUBLIC RELEASE