Optimization of Device Geometry for Rotating Detonation Engines

To study the impact of combustion chamber and nozzle geometries on the performance of rotating detonation engines, modifications will be made to an existing modular, experimental rotating detonation engine with variable geometry. The research proposed will follow a three phase plan, corresponding to the three sets of increasingly complex expansion devices. Phase 1 will constitute the modification of the test device for integration with expansion device interface, modification of the test stand and instrumentation to allow thrust measurement, design of interfaces required for testing, and the design, additive manufacturing, and testing of an initial set of simple geometry expansion devices. The visiting technologist experience would allow for collaboration with NASA in the design and manufacture of the nozzle set as well as in defining the operating conditions for testing. Phase 2 will constitute the intensive design, additive manufacturing, and testing of a second set of nozzles, informed by results obtained from phase 1 testing. This second set of nozzles is intended to provide the bulk of the data for this project. Phase 3 mainly constitutes analysis and modeling of the data, but will also involve design, testing, and manufacture of a smaller and more focused set of third nozzles with more complex geometries compared to phase 1 and 2 nozzles. This set is intended to explore geometric relations observed, but not comprehensively tested for, in phase 2, the analysis of phase 1 and 2 test data, and the comprehensive modeling of the resulting test data, thus achieving the objective of this research proposal. This research will provide engineers the tools they need to create optimally designed combustion chambers and additively manufactured expansion devices for rotating detonation engines, representing a significant step towards practical hypersonic flight, lower-cost access to space, and compact, highly power-dense in-space propulsion systems.

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