Accession Number:

ADA540028

Title:

Detonation Propagation Through Ducts in a Pulsed Detonation Engine

Descriptive Note:

Master's thesis

Corporate Author:

AIR FORCE INST OF TECH WRIGHT-PATTERSON AFB OH GRADUATE SCHOOL OF ENGINEERING AND MANAGEMENT

Personal Author(s):

• Nielsen, Jeffrey M.

Report Date:

2011-03-01

Pagination or Media Count:

88.0

Abstract:

Development of a continuously operating pulsed detonation engine PDE without a high energy ignition system or a deflagration-to- detonation transition DDT device will increase engine efficiency, reduce cost, improve performance, and reduce weight. This report is a study of configurations that allow a consistent and predictable transition of a detonation from one detonation tube to second tube. The intent was, via visualization of detonation propagation through a cross-over tube, to develop a cross-over passage leading to minimization of energy losses and effective and repeatable tube-to-tube initiation. Detonation tube cross-over width, cross-over geometry and fuels were varied to determine their effect on tube-to-tube detonation initiation. The cross-over detonations studied decoupled into and out of the cross-over tube due to propagation as subcritical spherical detonations. It was shown that the mechanism of shock reflection could be used to transition the spherical detonation back to a planar detonation.

Descriptors:

• *PULSEJET ENGINES
• SHOCK WAVES
• THESES
• REFLECTION
• COMBUSTION
• TRANSITIONS
• DETONATIONS
• TUBES
• PROPAGATION
• HIGH ENERGY

Subject Categories:

• Jet and Gas Turbine Engines

Distribution Statement:

APPROVED FOR PUBLIC RELEASE