Build Up and Operation of an Axial Turbine Driven by a Rotary Detonation Engine
AIR FORCE INST OF TECH WRIGHT-PATTERSON AFB OH GRADUATE SCHOOL OF ENGINEERING AND MANAGEMENT
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Detonation combustors provide advantages over current deflagration combustors due to their pressure gain and simplicity of design. Rotary detonation engines RDEs offer advantages over pulsed detonation engines PDEs due to a steadier exhaust and fewer total system losses. All previous research on turbine integration with detonation combustors has focused on utilizing PDEs to drive axial and centrifugal turbines. The objective of this thesis was the integration and testing of an axial turbine driven by a rotary detonation engine RDE to determine turbine operability. In pursuit of this objective, convergent nozzle sections were placed on the RDE to simulate the back-pressurization that would occur when placing the turbine behind the RDE. Nozzle testing showed that back-pressurizing the RDE increases the operational space of the RDE. Results from the nozzle testing were used to properly integrate the turbine with the RDE. The turbine was driven by the RDE with successful detonation runs, showing turbine operation with RDEs is possible. The RDE operated similarly for both nozzle and turbine testing, demonstrating that a nozzle can properly simulate the presence of a turbine behind a RDE.
- Jet and Gas Turbine Engines