Dynamic fluidic nozzles for pulse detonation engine applications

Download
Author
McClure, James R. III
Date
2010-03Advisor
Brophy, Christopher M.
Second Reader
Hobson, Garth V.
Metadata
Show full item recordAbstract
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.
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.Collections
Related items
Showing items related by title, author, creator and subject.
-
Fluidically augmented nozzles for pulse detonation engine applications
Smith, Larry R. (Monterey, California. Naval Postgraduate School, 2011-12);Pulse Detonation Engines (PDE) operate in a cyclic manner resulting in large changes in the combustion chamber pressure. The widely varying pressure ratio between the chamber and nozzle exit makes it difficult to efficiently ... -
Particle behavior in solid propellant rocket motors and plumes
McCrorie, J. David. II (Monterey, California. Naval Postgraduate School, 1992-12);The particle size distribution inside the combustion chamber and the changes that occurred across the exhaust nozzle were measured in a subscale solid propellant rocket motor with a 2% aluminized end-burning propellant ... -
Pressure distribution and performance impacts of aerospike nozzles on rotating detonation engines
Schnabel, Mark C. (Monterey, California: Naval Postgraduate School, 2017-06);Rotating detonation engines (RDEs) have the potential to further increase the performance of air-breathing propulsion devices and are currently being explored as an option for missions with wide altitude and flight Mach ...