Pressure Distribution and Performance Impacts of Aerospike Nozzles on Rotating Detonation Engines
Schnabel, Mark C.
Brophy, Christopher M.
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Rotating detonation engines (RDE) 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 number ranges. Aerospike nozzles lend themselves well to this type of application because they possess altitude-compensating characteristics. However, the effects of the unsteady nozzle inlet dynamics associated with RDEs on aerospike nozzle performance have not been fully determined. Consequently, aerospike nozzle design has not yet been optimized for RDE applications. A contoured aerospike nozzle was designed for implementation on a RDE to examine the effect of ideal aerospike profiles on RDE performance. Currently, no simple nozzle design technique accounts for transient throat conditions inherent in RDE operation. Therefore, a nozzle contour was designed using a traditional, steady-state design methodology at both on- and off-design conditions anticipated throughout the combustion cycle. Steady-state, non-reacting computational fluid dynamics (CFD) simulations were performed on various nozzle geometries over multiple pressure ratios to investigate the flow field structure along the nozzle contour and justify design tradeoffs. Experimental thrust and nozzle contour pressure measurements will be used to determine the applicability of first-order design tools for performance estimation
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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 ...
Effect of pressure and temperature on oil mist sprays used for blade excitation in high cycle fatigue testing Thompson, Andrew P. (Monterey California. Naval Postgraduate School, 2006-06);The flow patterns of two oil mist nozzles used in rotor blade excitation experiments were characterized using a Laser Doppler Velocimeter (LDV). Both nozzles were operated in a vacuum test chamber and velocity measurements ...
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 ...