Experimental study on the wall temperature and heat transfer of a two-phase pulse detonation rocket engine

Yongjia, Wang; Wang, Ke; Fan, Wei; He, Jianjia; Zhang, Yang; Zhang, Qibin; Yao, Kuiguang

doi:10.1016/j.applthermaleng.2016.12.001

Cited by 24 publications

(2 citation statements)

References 14 publications

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“…Adding additives in the liquid kerosene also can shorten the detonation time and increase the explosibility of fuel materials. Recently, Wang et al [64] studied the temperature distribution and thermal load in two-phase PDRE through a series of experiments. The thermal load in the propagation stage distributes evenly, but it distributes unevenly in the DDT stage.…”

Section: Oil Supplymentioning

confidence: 99%

Research Progresses of Flash Evaporation in Aerospace Applications

Ma¹,

Zhai

Zhang

et al. 2018

International Journal of Aerospace Engineering

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Liquid is overheated and evaporated quickly when it enters into the environment with lower saturation pressure than that corresponding to its initial temperature. This phenomenon is known as the flash evaporation. A natural low-pressure environment and flash evaporation have unique characteristics and superiority in high altitude and outer space. Therefore, flash evaporation is widely used in aerospace. In this paper, spray flash evaporation and jet flash evaporation which are two different forms were introduced. Later, key attentions were paid to applications of flash evaporation in aerospace. For example, the flash evaporation has been used in the thermal control system of an aircraft and the propelling system of a microsatellite and oil supply system of a rocket motor. Finally, the latest progresses in the calculation model and numerical simulation of flash evaporation were elaborated.

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Section: Oil Supplymentioning

confidence: 99%

Research Progresses of Flash Evaporation in Aerospace Applications

Ma¹,

Zhai

Zhang

et al. 2018

International Journal of Aerospace Engineering

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“…Detonation combustion has attracted plenty of attention from researchers because of its high thermal efficiency, low entropy generation and self-pressurization characteristic [1,2]. According to the formation process of detonation waves and operating characteristics in the engines, detonation engines can be divided into rotating detonation engine (RDE) [3,4], pulse detonation engine (PDE) [5,6] and standing detonation wave engine (SDWE) [7]. The detonation initiation technology is one of the bottlenecks and key technologies that restrict the engineering application of any detonation engines.…”

Section: Introductionmentioning

confidence: 99%

Numerical Simulation of Hot Jet Detonation with Different Ignition Positions

et al. 2019

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Ignition position is an important factor affecting flame propagation and deflagration-to-detonation transition (DDT). In this study, 2D reactive Navier–Stokes numerical studies have been performed to investigate the effects of ignition position on hot jet detonation initiation. Through the stages of hot jet formation, vortex-flame interaction and detonation wave formation, the mechanism of the hot jet detonation initiation is analyzed in detail. The results indicate that the vortexes formed by hot jet entrain flame to increase the flame area rapidly, thus accelerating energy release and the formation of the detonation wave. With changing the ignition position from top to wall inside the hot jet tube, the faster velocity of hot jet will promote the vortex to entrain jet flame earlier, and the DDT time and distance will decrease. In addition, the effect of different wall ignition positions (from 0 mm to 150 mm away from top of hot jet tube) on DDT is also studied. When the ignition source is 30 mm away from the top of hot jet tube, the distance to initiate detonation wave is the shortest due to the highest jet intensity, the DDT time and distance are about 41.45% and 30.77% less than the top ignition.

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Investigation on the propagation process of rotating detonation wave

Deng

et al. 2017

Acta Astronautica

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Experimental study on the wall temperature and heat transfer of a two-phase pulse detonation rocket engine

Cited by 24 publications

References 14 publications

Research Progresses of Flash Evaporation in Aerospace Applications

Research Progresses of Flash Evaporation in Aerospace Applications

Numerical Simulation of Hot Jet Detonation with Different Ignition Positions

Investigation on the propagation process of rotating detonation wave

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