Approved for public release; distribution is unlimited. / An efficient nozzle design is critical for enhancing the benefits of Pulse Detonation Engines (PDEs) and enabling
their use as future propulsion or power generation systems. Due to the inherent variation in chamber pressure for
Pulse Detonation Combustors, it has been difficult to design a nozzle, which has the capability to provide an
appropriate exit-to-throat area ratio suited for both the detonation blow-down event and refresh pressures associated
with the cyclic operation of a PDE. A two-dimensional PDE exit nozzle was designed, modeled, and constructed in
an attempt to increase the overall efficiency of converting thermal energy to kinetic energy by providing a fluidic
method to dynamically vary the effective nozzle area ratio. A fluidic nozzle configuration was evaluated, which had
the ability to inject a small amount of air into the diverging section of the nozzle in order to dynamically create a more
desirable exit-to-throat area ratio. Experimental testing was conducted on various injection flow rates, and a
shadowgraph system was used to observe the fluid flow characteristics within the nozzle. Computer simulations were
used to analyze the fluid flow properties within the nozzle. A comparison of the computer simulations and the
experimental results was performed and demonstrated good agreement. / Lieutenant, United States Navy
| Identifer | oai:union.ndltd.org:nps.edu/oai:calhoun.nps.edu:10945/55200 |
| Date | 03 1900 |
| Creators | McClure, James R. III |
| Contributors | Brophy, Christopher M., Hobson, Garth V., Mechanical and Aerospace Engineering |
| Publisher | Monterey, California. Naval Postgraduate School |
| Source Sets | Naval Postgraduate School |
| Detected Language | English |
| Type | Thesis |
| Format | application/pdf |
| 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. |
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