Effects of supersonic nozzle guide vanes on the performance and flow structures of a rotating detonation combustor

• Published in: Acta astronautica 2022-04, Vol.193, p.90-99
• Main Authors: Shen, Dawen, Cheng, Miao, Wu, Kevin, Sheng, Zhaohua, Wang, Jianping
• Format: Article
• Language: English
• Subjects: Combustion chambers; Configuration management; Damping; Detonation; Flow structures; Guide vanes; Leading edges; Pressure drop; Pressure gain combustion; Rotating detonation combustor; Rotation; Shock wave propagation; Shock wave reflection; Shock waves; Supersonic nozzle guide vane; Supersonic nozzles; Turbine engines; Turbines
• ISSN: 0094-5765; 1879-2030
• DOI: 10.1016/j.actaastro.2022.01.002

The integration of a rotating detonation combustor with downstream nozzle guide vanes is a crucial early step prior to the full implementation of the rotating detonation turbine engine. The present study aims to elucidate the flow structures introduced by this integration and provide guidance for the application of rotating detonation turbine engines. A numerical investigation on a rotating detonation combustor with three supersonic guide vane configurations is conducted and compared to a baseline case without any nozzle guide vane. Integrating nozzle guide vanes into the rotating detonation combustor increases the detonation strength and its pressure gain capability, resulting in a higher outlet total pressure for the greater thrust potential. The results show that the total pressure drops mainly in the attached oblique shock region rather than the nozzle guide vane passages. Moreover, the detonation intensity and the shock structures in nozzle guide vane passages influence the total pressure gain performance for multiple configurations. Compared to others, the aligned configuration is preferred for future design due to the optimal comprehensive performance of unsteadiness damping, flow conditioning, total pressure gain, and useful work production. Furthermore, a shock structure termed rake-type shock envelope is identified for the first time. The propagating detonation forces the reflected shock waves from the leading edges of the vanes to move circumferentially, yielding this dynamic shock system. This suggests that the propagating detonation guarantees no normal shocks upstream of the nozzle guide vanes, and therefore the typical unstarting issue for turbines is prevented. •Simulations on a rotating detonation combustor configured with supersonic nozzle guide vanes are performed.•Performance assessments among multiple configurations are conducted.•A dynamic shock structure termed rake-type shock envelope is identified for the first time.•Numerical results provide guidance for the rotating detonation turbine engine.