In order to study the influences of axial and circumferential lengths of rotating detonation engine combustion chamber on gas-liquid two-phase rotating detonation characteristics

the theoretical model of gasoline/oxygen-enriched air two-phase rotating detonation with chemical reaction was solved by conservative element and solution element (CE/SE) method. The flow field structure of gas-liquid two-phase rotating detonation was obtained

and the influences of the axial and circumferential lengths of the combustion chamber on the flow field

detonation wave propagation characteristics and thrust performance of the engine were analyzed. The calculation results showed that the axial length had little effect on the upstream flow field of the combustion chamber

but had a significant effect on the downstream flow field parameters. With the increase of the axial length

the outlet pressure

temperature

density and circumferential velocity of the combustion chamber decreased

while the axial velocity increased gradually

and the average thrust density and fuel specific impulse of the engine increased first and then decreased. When the circumferential length was too short

it was difficult to form a self-sustaining propagating detonation wave in the combustion chamber. As the circumferential length increased

the strength of upstream detonation wave increased

and the corresponding flow field parameters increased

however

the thrust performance of engine decreased slightly.