The effects of particulates on supersonic shear layers and afterburning in fuel-rich plumes
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Authors
Lee, Siwon R.
Subjects
Advisors
Netzer, David W.
Date of Issue
1995-12
Date
December 1995
Publisher
Monterey, California. Naval Postgraduate School
Language
en_US
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.
Type
Thesis
Description
Series/Report No
Department
Astronautical Engineering
Organization
Identifiers
NPS Report Number
Sponsors
Funder
Format
44 p.
Citation
Distribution Statement
Rights
This publication is a work of the U.S. Government as defined in Title 17, United States Code, Section 101. Copyright protection is not available for this work in the United States.