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      Design of a Premixed Fuel–Oxidizer System to Arrest Flashback in a Rotating Detonation Engine


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          Rotating detonation engines offer the promise of pressure gain combustion in aeronautical combustors where (normally) stagnation pressure decreases. For practical reasons, current experimental rotating detonation engine designs include separate streams of fuel and air injected into a detonation channel. Experimentation with a fully premixed rotating detonation engine has repeatedly failed due to flame flashback into the premixed plenum. That fundamental problem is the subject of this paper: understanding the relevant principles and parameters that contribute to flashback and investigating a scheme for arresting the flashback phenomenon. This investigation quantifies the flashback susceptibility for a proposed rotating detonation engine feed slot with parameterization of channel height, channel length, equivalence ratio, fuel type, and feed pressure. The design principles of quenching distance and critical boundary-layer velocity gradients are shown to describe the safe operation region to deliver a safe premixture of fuel and air to a rotating detonation engine when adjusted for experimental conditions and applied in unison. This research leads to a design that is capable of avoiding flashback while enabling detonation to occur in a rotating detonation engine.

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          Most cited references24

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          Rotating Detonation Wave Propulsion: Experimental Challenges, Modeling, and Engine Concepts

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            Experimental determination of counterflow ignition temperatures and laminar flame speeds of C2–C3 hydrocarbons at atmospheric and elevated pressures

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              Experimental and numerical study on laminar burning velocities and flame instabilities of hydrogen–air mixtures at elevated pressures and temperatures


                Author and article information

                Journal of Propulsion and Power
                J. Propulsion
                American Institute of Aeronautics and Astronautics
                30 January 2017
                September–October 2017
                : 33
                : 5
                : 1063-1073
                Air Force Institute of Technology , Wright–Patterson Air Force Base, Ohio 45433
                U.S. Air Force Research Laboratory , Wright–Patterson Air Force Base, Ohio 45433
                Innovative Scientific Solutions, Inc. , Dayton, Ohio 45459
                Author notes

                Graduate Student, Department of Aeronautics and Astronautics. Student Member AIAA.


                Professor, Department of Aeronautics and Astronautics. Senior Member AIAA.


                Professor, Department of Aeronautics and Astronautics. Associate Fellow AIAA.


                Mechanical Engineer, Propulsion Directorate, AFRL/RQTC. Associate Fellow AIAA.


                Research Engineer. Associate Fellow AIAA.

                B36259 B36259
                This material is declared a work of the U.S. Government and is not subject to copyright protection in the United States. All requests for copying and permission to reprint should be submitted to CCC at www.copyright.com; employ the ISSN 0748-4658 (print) or 1533-3876 (online) to initiate your request. See also AIAA Rights and Permissions www.aiaa.org/randp.
                Page count
                Figures: 14, Tables: 0
                Full-Length Paper

                Engineering,Physics,Mechanical engineering,Space Physics
                Engineering, Physics, Mechanical engineering, Space Physics


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