Sijia Gao, Han Peng, Yue Huang, Zhipeng Sun, Yancheng You
DOI Number: XXX-YYY-ZZZ
Conference number: HiSST2024-00173
In order to investigate the interaction between the detonation wave and the upstream airflow, a
non-premixed air-breathing rotating detonation combustor with an axial inlet was simulated by using
the Navier-Stokes equation of two-dimensional unsteady reaction, a complete structure of rotating
detonation wave and upstream flow field was obtained, and the interaction between the detonation
wave and the upstream airflow was analyzed by a combination of equation derivation and numerical
simulation. The equations for calculating the airflow velocity after the forward shock wave and the
height of detonation wave were derived and verified. The results show that the rotating detonation
wave would trigger the forward shock wave propagating in the upstream, and the velocity would be
weakened and the direction would be deflected of the airflow passing through the forward shock wave.
If the airflow velocity drops to a negative value after passing the forward shock wave, there will be no
air injection into the combustor. The velocity of the airflow after the forward shock wave is inversely
proportional to the velocity of the detonation wave, the temperature of the incoming airflow and the
pressure ratio at the forward shock wave. The angle of the forward shock wave is inversely proportional
to the velocity of the detonation wave. The interaction between detonation wave and incoming flow is
summarized, the higher the intensity of the detonation wave, the slower the recovery time of the airflow
after the forward shock wave, and the lower the height of the detonation wave.