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dc.contributor.advisorWilson, Donald
dc.creatorGopalakrishnan, Nandini
dc.date.accessioned2017-10-02T15:02:52Z
dc.date.available2017-10-02T15:02:52Z
dc.date.created2017-08
dc.date.issued2017-08-21
dc.date.submittedAugust 2017
dc.identifier.urihttp://hdl.handle.net/10106/26998
dc.description.abstractRotating detonation engines (RDE) have received considerable research attention in recent times for use in propulsion systems. The cycle frequency of operation of an RDE can be as high as 10,000 Hz. Conventional mechanical valves cannot operate at such high frequencies, leading to the need for propellant injectors or valves with no moving parts. A fluidic valve is such a valve and is the focus of this study. The valve consists of an orifice connected to a constant area plenum cavity which operates at constant pressure. The fluidic valve supplies propellants to the detonation tube through the orifice. Hydrogen – oxygen detonation is studied in a tube with fluidic valves. A detailed 19-step chemical reaction mechanism has been used to model detonation and the flow simulated in ANSYS Fluent. This research aims to determine the location of contact surface in the cavity and the time taken for the contact surface to leave the valve after a shock wave has passed through it. This will help us understand if the steady-state flow in the cavity is comprised of detonation products or fresh propellants.
dc.format.mimetypeapplication/pdf
dc.language.isoen_US
dc.subjectFluidic valve
dc.subjectDetonation engine
dc.titleNumerical simulation of flow in fluidic valves in rotating detonation engines
dc.typeThesis
dc.date.updated2017-10-02T15:03:23Z
thesis.degree.departmentMechanical and Aerospace Engineering
thesis.degree.grantorThe University of Texas at Arlington
thesis.degree.levelMasters
thesis.degree.nameMaster of Science in Aerospace Engineering
dc.type.materialtext
dc.creator.orcid0000-0003-4427-5201


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