Accession Number : ADA311789
Title : The Effects of Particulates on Supersonic Shear Layers and Afterburning in Fuel-Rich Plumes.
Descriptive Note : Master's thesis,
Corporate Author : NAVAL POSTGRADUATE SCHOOL MONTEREY CA
Personal Author(s) : Lee, Siwon R.
PDF Url : ADA311789
Report Date : DEC 1995
Pagination or Media Count : 58
Abstract : An investigation was conducted to experimentally quantify the interaction of particulates with the fuel-rich plume flowfield typical for solid propellant rocket motors. This was done in order to optimize enhanced mixing devices or chemical-additive addition for afterburning suppression. Laser sheet flow visualization, sound spectra measurements, plume thermal images and particle size distribution measurements were utilized with reacting and non-reacting gaseous plumes and with the plumes from highly aluminized propellant and minimum smoke propellant. Several devices were evaluated for their effectiveness in providing increased mixing in the supersonic shear layer. It was found that the generation of axial vortices in the supersonic shear layers at the nozzle exit of rocket motors operating with characteristically high exit Mach numbers and high temperatures can enhance the mixing rates and affect the afterburning. The presence of large quantities of particulates both in the shear layer and in the plume core appears to significantly change the results obtained using enhanced mixing devices. Initial results with a ramp nozzle indicate that enhanced large-scale mixing can be provided in the presence of high particulate loadings in the plume.
Descriptors : *SUPERSONIC FLOW, *EXHAUST PLUMES, *SOLID PROPELLANT ROCKET ENGINES, *AFTERBURNING, PRESSURE GRADIENTS, PARTICLE SIZE, OPTIMIZATION, HIGH TEMPERATURE, THESES, VORTICES, FLOW VISUALIZATION, FLOW FIELDS, TEMPERATURE GRADIENTS, ACOUSTIC MEASUREMENT, PARTICULATES, FUEL AIR RATIO, MACH NUMBER, THERMAL IMAGES, NOZZLE GAS FLOW, SHEAR FLOW, CAVITATION, JET MIXING FLOW, COMBUSTION PRODUCTS, ALUMINIZED PROPELLANTS.
Subject Categories : Fluid Mechanics
Combustion and Ignition
Solid Propellant Rocket Engines
Distribution Statement : APPROVED FOR PUBLIC RELEASE