Accession Number : AD0836803
Title : A SHOCK TUBE STUDY OF THE IGNITION LIMIT OF BORON PARTICLES.
Descriptive Note : Master's thesis,
Corporate Author : AIR FORCE INST OF TECH WRIGHT-PATTERSON AFB OH SCHOOL OF ENGINEERING
Personal Author(s) : Uda, Robert T.
Report Date : JUN 1968
Pagination or Media Count : 100
Abstract : A shock tube study was conducted to determine the ignition limit of clouds of boron particles. The ignition limit is an experimentally determined curve, plotted on temperature-pressure coordinates, separating the ignition and no ignition zones. A 3-inch inside diameter constant area shock tube employing a helium/air gas system was used for igniting the boron particles. The particles were ignited in the high temperature region behind the reflected shock wave. The boron samples used were 30-50 micron diameter agglomerates (1-2 micron primary particles) and 0.015 micron diameter particles. Ignition delay time of 0.015 micron particles was also obtained. (Author)
Descriptors : *FUEL ADDITIVES), (*SUPERSONIC COMBUSTION RAMJET ENGINES, (*BORON, IGNITION), (*SHOCK TUBES, BORON), SUPERSONIC COMBUSTION, PARTICLES, TEMPERATURE, TWO PHASE FLOW, SHOCK WAVES, THESES, SOLID ROCKET PROPELLANTS.
Subject Categories : Test Facilities, Equipment and Methods
Combustion and Ignition
Jet and Gas Turbine Engines
Distribution Statement : APPROVED FOR PUBLIC RELEASE