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:

1968-06-01

Pagination or Media Count:

100.0

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 heliumair 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