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