Structure of Partially Premixed Flames and Advanced Solid Propellants.
Abstract
The combustion of solid rocket propellants of advanced energetic materials involves a complex process of decomposition and condensed phase reactions in the solid propellant, gaseous flame reactions above the propellant surface, and subsequent mixing and flow through the combustion chamber. The response to combustion instabilities is influenced by the structure of the premixed and partially premixed diffusion flames and triple flames at the propellant surface. This research provided experimental data and modeling of partially premixed diffusion flames supported by nitrogen oxides that are common with advanced solid propellants. Of particular interest was the stability and possible extinction of the flames in the presence of velocity fluctuations across the propellant. It was shown that premix flames of highly disparate equivalence ratio can be supported in opposed-flow geometry and will form a triple flame structure. Evidence was presented which indicates that a diffusion flame forms between the premix flames and is due to the conversion of H2, O2, and CO originating from the premix flame zones to H20 and CO2.
Document Details
- Document Type
- Technical Report
- Publication Date
- Nov 30, 1998
- Accession Number
- ADA367085
Entities
People
- Christopher B. Dreyer
- Melvyn C. Branch
Organizations
- University of Colorado Boulder