Abstract
In this work, the integration of supersonic turbomachinery with rotating detonation combustors is analyzed. First, a two-dimensional unsteady Reynolds-Averaged Navier-Stokes simulation of a rotating detonation combustor is presented and compared to experiments. The unsteady outlet of the RDC is then used as inlet condition for the 3D non-reactive URANS simulations to investigate the influence of a divergent nozzle downstream of the combustor. Influence of the nozzle on flow angle and total pressure loss during several periods of the rotating detonation wave are computed and compared with steady simulations. To further mitigate the unsteady flow behavior, supersonic stators are used and its flow field is studied. Finally, the implementation of the supersonic stator vanes in the Turbine-Integrated High-Pressure Optical RDE (THOR) test platform is described.
| Original language | English (US) |
|---|---|
| Title of host publication | AIAA Propulsion and Energy Forum and Exposition, 2019 |
| Publisher | American Institute of Aeronautics and Astronautics Inc, AIAA |
| ISBN (Print) | 9781624105906 |
| DOIs | |
| State | Published - 2019 |
| Externally published | Yes |
| Event | AIAA Propulsion and Energy Forum and Exposition, 2019 - Indianapolis, United States Duration: Aug 19 2019 → Aug 22 2019 |
Publication series
| Name | AIAA Propulsion and Energy Forum and Exposition, 2019 |
|---|
Conference
| Conference | AIAA Propulsion and Energy Forum and Exposition, 2019 |
|---|---|
| Country/Territory | United States |
| City | Indianapolis |
| Period | 8/19/19 → 8/22/19 |
Bibliographical note
Publisher Copyright:© 2019, American Institute of Aeronautics and Astronautics Inc, AIAA. All rights reserved.
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