American Institute of Aeronautics and Astronautics 1 Thermodynamic Modeling of a Rotating Detonation Engine Craig A. Nordeen 1 and Douglas Schwer 2 University of Connecticut, Storrs, CT 06269-3139 Naval Research Laboratory, Washington, DC 20375 Fredrick Schauer 3 and John Hoke 4 Air Force Research Laboratory, Wright-Patterson AFB, OH, 45433 Innovative Scientific Solutions Inc., Dayton, OH, 45440 and Baki Cetegen 5 and Thomas Barber 6 University of Connecticut, Storrs, CT 06269-3139, USA In pursuit of greater thermal and propulsive efficiencies in rockets or gas turbines, a one- dimensional thermodynamic model of a Rotating Detonation Engine (RDE) is compared to a numerical simulation model with good results. A ZND detonation model is modified to include stagnation properties and account for the velocity vectors that occur upstream of the detonation. Features of the RDE and their impact on the model are discussed. Velocity triangles, commonly used in the gas turbine industry, are shown to be an effective tool for understanding energy transfer in RDE’s. I. Introduction continuous detonation or rotating detonation engine (RDE) utilizes supersonic combustion phenomena that may deliver as much as a 20% increase in propulsive or thermal efficiency over conventional methods. 1 A RDE contains a detonation wave that propagates continuously around an annular combustion chamber, while a fuel and oxidizer mixture is delivered continuously as shown in Fig. 1. The exhaust is continuous supersonic flow with a rotating pressure wave. The increase in efficiency is expressed as a higher kinetic energy, rather than an increase in pressure. Possible applications may be found in rockets or gas turbine combustion chambers. The idea and first embodiment of a continuous detonation device was conceived in the 1950’s. Early work at the Lavrent’ev Institute of Hydrodynamics in Siberia 2 and the University of Michigan 3 explored the possibilities of such a device. Today experimental and theoretical work continues at more than a dozen institutions worldwide. 4,5 The continuous nature of the flow is more compatible with existing propulsion technology when compared with pulse detonation engines (PDE). The simplicity of the device eliminates several issues inherent in typical PDEs. Except for the initial start sequence, ignition and transition to detonation issues are eliminated, and detrimental vibration effects are reduced. Mechanical valves are eliminated, and complexity is reduced to nonmoving parts. 1 Graduate Assistant, Mechanical Engineering, 191 Auditorium Rd, UConn, Storrs, 06269, AIAA Member. 2 Mechanical Engineer, Center for Reactive Flow and Dynamical Systems, Code 6410, AIAA Member. 3 Research Engineer, Propulsion Directorate, 1790 Loop Rd., Dayton, OH 45433, AIAA Senior Member 4 Senior Engineer, 2766 Indian Ripple Rd., Dayton, OH 45440, AIAA Senior Member 5 Professor and Department Head, Mechanical Engineering, 191 Auditorium Rd, UConn, Storrs, 06269 6 Professor-in-Residence, Mechanical Engineering, 191 Auditorium Rd, UConn, Storrs, 06269, AIAA Associate Fellow A Figure 1. 3-D RDE simulation. 49th AIAA Aerospace Sciences Meeting including the New Horizons Forum and Aerospace Exposition 4 - 7 January 2011, Orlando, Florida AIAA 2011-803 Copyright © 2011 by the American Institute of Aeronautics and Astronautics, Inc. All rights reserved.