Accession Number : AD0844310
Title : Investigation of Air-Augmented Rocket Combustion and Mixing Processes.
Descriptive Note : Final technical rept. Sep 66-Jul 68,
Corporate Author : ATLANTIC RESEARCH CORP ALEXANDRIA VA
Personal Author(s) : Sargent, W. H. ; Woodcock, K. E. ; Anderson, R. S. ; Duvvuri, T.
Report Date : AUG 1968
Pagination or Media Count : 291
Abstract : The results of an experimental and theoretical study of coaxial jet mixing and combustion are presented. The characteristics of a primary stream were systematically varied through a broad range of conditions and the exchange processes occuring in a secondary chamber were observed by means of wall pressure measurements, wall calorimeters and chemical sampling. Primary stream variables studied include temperature (1000-3000K), chemical reactivity (0-400 kcal/100g), particulate matter content (0-50 percent), particle diameter (2,200 microns), radio of gas phase to solid phase reactivity (0-1), primary stream momentum, and exit plane geometry. Secondary stream parameters studied were velocity (500-1000 ft/sec) and temperature (300 - 1000K). Analysis of the data shows that the length of the duct required for momentum and energy exchange is dominated in all instances primarily by secondary air mass flow. The data also show that boron combustion efficiency is highly dependent upon primary and secondary stream temperature. Combustion efficiency data were able to be correlated assuming a diffusion controlled heterogeneouse combustion process. An analytical treatment of a two-phase mixing process in the region of the potential core is presented and wall static pressures computed over this region are compared with experimentally determined trends. (Author)
Descriptors : *COMBUSTION), *JET MIXING FLOW), (*LIQUID PROPELLANT ROCKET ENGINES, (*COMBUSTION CHAMBER GASES, AIR, INJECTION, INTERIOR BALLISTICS, ENGINE AIR SYSTEMS COMPONENTS, TWO PHASE FLOW, PARTICLES, BORON, DUCTS, CALORIMETRY, COMBUSTION PRODUCTS, IGNITION, COMPUTER PROGRAMS.
Subject Categories : Combustion and Ignition
Liquid Propellant Rocket Engines
Distribution Statement : APPROVED FOR PUBLIC RELEASE