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

Report Date:

1994-03-29

Pagination or Media Count:

151.0

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.

Subject Categories:

  • Acoustics
  • Combustion and Ignition
  • Solid Propellant Rocket Engines

Distribution Statement:

APPROVED FOR PUBLIC RELEASE