Experimental study on propagation characteristics of rotating detonation wave with kerosene fuel-rich gas

Han, Jiaxiang; Bai, Qiaodong; Zhang, Shijian; Wang, Fang; Wang, Chunsheng

doi:10.1016/j.dt.2022.04.004

Cited by 17 publications

(5 citation statements)

References 24 publications

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“…We select zones A, B and C near the discontinuities for more detailed analysis. In the enlarged view of Zone A, it can be observed that there are two low PCB3 pressure signals before and after each pressure peak measured by PCB1, which is a typical tow-counter RDW mode [18][19][20], and the collision point is near PCB1. In the enlarged view of Zone B, it can be found that there is also a typical tow-counter RDW mode pressure signal, but the collision point is transferred to PCB3.…”

Section: Fig5 Pressure Signal Of Discontinuous Detonation In Casementioning

confidence: 99%

“…Meng et al [17] studied the influence of oxidant mass flow on propagation characteristics by controlling the equivalence ratio at about 0.7, and found that when the oxidant flow increased, the mode changed from single wave to double wave, and the stability of RDW was improved. Han et al [18] used a gas generator to obtain kerosene pyrolysis gas, and obtained stable RDW when the oxygen content of oxidant was higher than 36%. Ding et al [19] used kerosene as fuel in combination with high-speed photography, and observed single wave, two-counter RDW mode and four-counter RDW mode in RDE.…”

Section: Introductionmentioning

confidence: 99%

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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: Fig5 Pressure Signal Of Discontinuous Detonation In Casementioning

confidence: 99%

Section: Introductionmentioning

confidence: 99%

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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“…Yao and Zhou et al [23] established the thermal performance model of the variable-thrust liquid rocket engine and analyzed the influence of the main liquid rocket engine design parameters on the performance optimization, matched the LOX/kerosene propellants system parameters under a 100-20% variable-thrust operation, and conducted an analysis on the liquid rocket engine operating characteristics under a wide range of variable-thrust operations. Han J et al [24] conducted their experiments to investigate the propagation characteristics of the rotating detonation wave with fuel-rich gas generator, and the effects of the basic parameters on the rotating detonation KFRG. Song et al [25] implemented a kerosene combustion model to predict the combustion behavior in the specified oxidizer-to-fuel mixing ratio range of 0.3 to 0.4.…”

Section: Introductionmentioning

confidence: 99%

Effects of Local Mixing Ratios and Mass Flow Rates on Combustion Performance of the Fuel-Rich LOX (Liquid Oxygen)/kerosene Gas Generator in the ATR (Air Turbo Rocket) Engine

Zhang

Zhao

et al. 2023

Aerospace

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This paper presents a numerical simulation analysis of the flow and combustion characteristics of a fuel-rich LOX (liquid oxygen)/kerosene gas generator in an ATR (air turbo rocket) engine, examining the effects of local parameters on the combustion flow field and performance. The analysis considers variations in unit injector mixing ratios and unit mass flow rates. The results indicate that as the mixing ratio in the inner-ring injectors increases (while the mixing ratio in the middle-ring injectors decreases), the oxygen concentration area near the axis zone and the 50% radius zone of the gas generator expands. Conversely, the kerosene concentration area near the axis zone decreases while gradually increasing near the 50% radius zone. In the flow direction section, there is an inverse relationship between the variation trend of local temperature and the oxygen concentration in the local area. As the oxygen concentration increases, the temperature decreases. The temperature distribution across the cross-section of the gas generator exhibits a circular pattern. When the mixing ratio (or mass flow rates) of the unit injector are perfectly balanced, the temperature distribution becomes highly uniform. A larger disparity in flow rate between the inner ring injector and the middle ring injector leads to a lower combustion efficiency. This effect differs from the effect of the mixing ratio difference between the two injector rings. Increasing the mixing ratio in the inner-ring injectors (or decreasing the mixing ratio in the middle-ring injectors) initially leads to a rise in combustion efficiency, followed by a subsequent decline. The maximum combustion efficiency of 89.10% is achieved when the mixing ratio is set to Km-1 = 0.7 and Km-2 = 2.79, respectively. Increasing the flow rate in the inner-ring injectors (or decreasing the flow rate in the middle-ring injectors) initially leads to an improvement in combustion efficiency, followed by a subsequent reduction. The maximum combustion efficiency of 86.13% is achieved when the mass flow rate is set to m-1 = m-2 = 0.1 kg/s.

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“…Zhong [24,25] and Yang [26] used kerosene pre-combustion cracked gas and oxygen-enriched air (oxygen ratio of 50% and 30%) to achieve rotating detonation, and investigated the basic characteristics of the rotating detonation wave. Han et al [27] also conducted experiments on rotating detonation with kerosene-fuel-rich gas and oxygenenriched air and found that the minimum oxygen content that could successfully initiate and maintain the stable propagation of the detonation wave is 32%. According to these research results, it can be concluded that technical challenges still exist in liquid fuel rotating detonation due to the imperfect mixing of fuel and oxidant and the low chemical reaction activity of the fuel itself [21].…”

Section: Introductionmentioning

confidence: 99%

Experimental Study on Propagation Characteristics of Kerosene/Air RDE with Different Diameters

Song

Zhou

et al. 2022

Energies

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A series of experimental tests were carried out in order to study the propagation characteristics of a liquid kerosene rotating detonation engine (RDE) with different diameters. Distinguished characteristics of spatial and temporal instability were found in the large-scale RDE due to the uneven circumferential distribution of kerosene supply pressure. As for the two counter-waves detonation system, the 500 mm-diameter RDE maintains a higher detonation wave velocity due to its longer injection recovery time. However, the 220 mm-diameter RDE can obtain a larger equivalence ratio operation range, higher specific thrust, and higher specific impulse. In addition, compared with the deflagration combustion, the detonation combustion has higher chamber pressure and thrust under the same operational conditions.

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Experimental study on propagation characteristics of rotating detonation wave with kerosene fuel-rich gas

Cited by 17 publications

References 24 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

Effects of Local Mixing Ratios and Mass Flow Rates on Combustion Performance of the Fuel-Rich LOX (Liquid Oxygen)/kerosene Gas Generator in the ATR (Air Turbo Rocket) Engine

Experimental Study on Propagation Characteristics of Kerosene/Air RDE with Different Diameters

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