摘要: Detonation based engines promises higher theoretical thermal efficiency as compared to their deflagration based counterparts operating at similar working conditions. Rotating detonation engines flow field constitutes a particular ... 展开 Detonation based engines promises higher theoretical thermal efficiency as compared to their deflagration based counterparts operating at similar working conditions. Rotating detonation engines flow field constitutes a particular challenge due to the complex supersonic flow features and strong unsteadiness present within. In this regard, variation in engine performance and detonation wave structure following sudden injector pressure changes in rotating detonation engines are investigated based on 2D numerical studies using ANSYS Fluent. The injector pressure of premixed stoichiometrically Hydrogen-air stream is abruptly doubled and quadrupled while the detonation wave was stable. After the wave stability is achieved again, the injector pressure is reduced to its initial value. Sudden changed in the injection pressure increased the detonation wave height 39% and 147% with the double and quadruple increase of instantaneous injector pressure, respectively. The variation in the injection pressure resulted in a significant variation in unsteady thrust production. It has been calculated that 0.9 ms is needed for the detonation wave to become stable again at doubled injector pressure while this time window found to be insufficient for the detonation wave to stabilize in case of quadruple increase in injection pressure. Notable changes observed in Mach number and flow angle variation when the injection pressure augmented to higher values were also reported and discussed. 收起