Accession Number:

ADA158314

Title:

Multi-Dimensional Combustion Instability Analysis of Solid Propellant Rocket Motors.

Descriptive Note:

Final rept. 15 Mar 83-14 Mar 85,

Corporate Author:

ALABAMA UNIV IN HUNTSVILLE DEPT OF MECHANICAL ENGINEERING

Personal Author(s):

Report Date:

1985-05-15

Pagination or Media Count:

47.0

Abstract:

Analytical models are developed for the multi-dimensional combustion instability analysis of solid propellant rocket motors. This research was motivated by the need for improvement of the current practice in combusiton instability analysis. For example, the burning rates and response functions are affected by the extremely complex flowfield. The flow is three-dimensional or at least two-dimensional in axisymmetric geometries vortex motions and turbulent flows must be adequately calculated the coupling mechanism of acoustic and hydrodynamic wave oscillations and particle damping should be clarified. These flowfield phenomena, after all, are originated from the flame zone activities - oscillatory behavior of all field variables such as temperature, velocity, pressure, density of the gas, and fuel fractions. The response functions, which serve as boundary conditions for the flowfield can be calculated from the first and second order perturbation eigenvalue analyses of the flame zone governing equations. The effect of velocity coupling appears, naturally, in the second order nonlinear solutions. All calculations are carried out using the finite element method. Some of the findings are summarized.

Subject Categories:

  • Fluid Mechanics
  • Combustion and Ignition
  • Solid Propellant Rocket Engines

Distribution Statement:

APPROVED FOR PUBLIC RELEASE