In order to study the effect of different nozzles on the performance of rotating detonation engine(RDE)

a thrust test bed of RDE was designed. The inside and outside diameters of RDE combustor were 70mm and 80mm

respectively. The length of the combustor was 40mm. H2 and air were used as fuel and oxidant respectively. The fuel and oxidizer were separately supplied through arrays of orifices and slot

respectively with impinging jets to promote the mixing. The RDE was ignited by the high-energy spark plugs and the thrust was measured with a piezoelectric force sensor. In these experiments

the working performance of the engine with converging nozzle

diverging nozzle and the Laval nozzle was studied. The results show that: within RDE stability work scope

the converging nozzle is better than others in improving thrust performance when inlet mass flow rate is less than 0.126kg/s. Detonation wave velocity and the thrust performance of RDE increases with the increase of inlet mass flow rate. Detonation wave velocity and thrust of RDE all reach maximum when equivalence ratio reaches an optimal value. Specific impulse of RDE based on the mixture can reach 95.21s.