Air-breathing rotating detonation fueled by liquid kerosene in cavity-based annular combustor

Meng, Haolong; Xiao, Qiang; Feng, Wenkang; Ming-liang, WU; Han, Xinpei; Wang, Fang; Wang, Chunsheng; Zheng, Quan

doi:10.1016/j.ast.2022.107407

Cited by 59 publications

(7 citation statements)

References 56 publications

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“…4 (a) that with the increase of equivalence ratio, the frequency of detonation wave generally increases first and then decreases, and the highest frequency 2272hz appears in Case7. This is consistent with previous study [22]. In Fig.…”

Section: Effect Of Equivalence Ratiosupporting

confidence: 94%

Experimental study on propagation characteristics of rotating detonation wave of liquid kerosene with oxygen-enriched air

Han

Zheng

Huang

et al. 2023

J. Phys.: Conf. Ser.

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In order to study the propagation characteristics of rotating detonation wave (RDW) of liquid fuel, an experimental study was carried out with liquid kerosene at room temperature as fuel and oxygen-enriched air with oxygen volume fraction of 38.5% as oxidant in this paper. RDW with equivalence ratio in the range of 0.65~0.9 was successfully obtained by controlling kerosene mass flow, and a detailed analysis of propagation characteristics of RDW was carried out. The results show that with the increase of equivalence ratio, the propagation state of RDW gradually changes from the premature flameout of discontinuous detonation to the complete operation of continuous detonation. The flow blockage of the injectors will further worsen the mixing effect under low equivalence ratio conditions, resulting in the discontinuous detonation phenomenon of repeated flameout-initiation process in the combustion chamber. In this study, almost all detonation waves operate in two-counter RDW mode, except that there is a single wave mode in a short period after flameout-initiation process.

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Section: Effect Of Equivalence Ratiosupporting

confidence: 94%

Experimental study on propagation characteristics of rotating detonation wave of liquid kerosene with oxygen-enriched air

Han

Zheng

Huang

et al. 2023

J. Phys.: Conf. Ser.

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“…The self-sustain deflagration and RDW were observed. The realization of stable operation of a ramjet-mode RDE fueled by kerosene was reported by Meng et al [23] with a cavity configuration in the combustor. The maximum propagation velocity of the RDW was 1082 m/s, which is about 60% of the CJ value.…”

Section: Introductionmentioning

confidence: 82%

Experimental investigation of ethylene-fueled ramjet rotating detonation engine with an annular combustor

Feng

Zheng

Xiao

et al. 2023

J. Phys.: Conf. Ser.

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A ramjet-mode rotating detonation engine fueled by ethylene is designed to demonstrate the feasibility of rotating detonation organization in annular combustor under high-speed incoming flow condition. The incoming flow with the design total temperature of 860 K and Mach number of 2 at the isolator inlet is provided by an air-heater, and the total mass flow is about 1.0 kg/s. The results show that the ramjet rotating detonation engine can operate in detonation mode when the equivalence ratio (ER) is no less than 0.54. By high-frequency pressure analysis and optical observation, two propagation modes of detonation wave are observed: rotating detonation in the ER range of 0.54-0.71 and longitudinally pulsating detonation in the ER range of 0.82-0.97. In rotating detonation mode, the wave velocity increases as ER increases, and the detonation velocities are about 60% of the CJ value. In longitudinally pulsating detonation mode, the propagation frequencies of the detonation wave are in the range of 1010 Hz-1017 Hz, which is much lower than that in rotating detonation mode, and the upstream propagation velocity of the detonation wave is estimated as 964 m/s. In addition, the maximum static pressure in the combustor increases with the ER from 0.54 to 0.97, and reaches 0.24 MPa when ER is 0.97. When ER is no more than 0.58, the isolator can effectively suppress the back pressure in the combustor, while ER is no less than 0.71, the back pressure in the combustor affects the flow at the isolator inlet, which implies that the isolator design needs to be optimized.

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“…Frolov et al [12] conducted a series of air-breathing CRD engine experiments in a wind tunnel and verified that the CRD could self-sustain in hypersonic inflow conditions. Meng et al [13] experimentally obtained an air-breathing liquid-kerosene-air rotating detonations wave via a direct-connect facility under Mach 4 flight conditions and found that the detonation wave is located downstream of the cavity, owing to the characteristic distance required for the evaporation and mixing of liquid kerosene. Prior investigations have established that an air-breathing CRD engine exhibits potential for practical applications.…”

Section: Introductionmentioning

confidence: 99%

Experimental Investigation of a Cylindrical Air-Breathing Continuous Rotating Detonation Engine with Different Nozzle Throat Diameters

et al. 2022

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A continuous detonation engine with various exhaust nozzles, analogous to typical scramjet cavity combustors with variable rear-wall heights, was adopted to perform a succession of cylindrical air-breathing continuous rotating detonation experiments fueled by a non-premixed ethylene/air mixture. The results show that the detonation combustion was observed to self-sustain in the combustor through simultaneous high-speed imaging covering the combustor and isolator. A long test, lasting more than three seconds, was performed in this unique configuration, indicating that the cylindrical isolator–combustor engine exhibits potential for practical applications. Three distinct combustion modes were revealed with varied equivalent ratios (hybrid mode, sawtooth wave mode, and deflagration mode). The diameter of the nozzle throat was critical in the formation of rotating detonation waves. When the nozzle throat diameter was larger than the specific value, the detonation wave could not form and self-sustain. The upstream boundary of the shock train was supposed to be close to the isolator entrance in conditions of a high equivalence ratio and small nozzle throat diameter. In addition, it was verified that periodic high-frequency pressure oscillation could cause substantial impacts on the incoming flow as compared with the steady deflagration with the same combustor pressure.

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Air-breathing rotating detonation fueled by liquid kerosene in cavity-based annular combustor

Cited by 59 publications

References 56 publications

Experimental study on propagation characteristics of rotating detonation wave of liquid kerosene with oxygen-enriched air

Experimental study on propagation characteristics of rotating detonation wave of liquid kerosene with oxygen-enriched air

Experimental investigation of ethylene-fueled ramjet rotating detonation engine with an annular combustor

Experimental Investigation of a Cylindrical Air-Breathing Continuous Rotating Detonation Engine with Different Nozzle Throat Diameters

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