Spray Characteristics of Gelled Propellants in Novel Impinging Jet Injector

Yang, Lijun; Fu, Qing-fei; Zhang, Wei; Du, Mingyue; Tong, Ming-Xi

doi:10.2514/1.b34551

Cited by 25 publications

(7 citation statements)

References 16 publications

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“…The design of the injector could also be modified in this regard. However, although atomization of the gel propellant can be improved using other types of injectors, such as the impinging jet injector [46,55,56,62] and the swirl injector [47,88,89], those injectors should be employed with care, especially in a small-scale thruster with a catalyst bed, since they potentially increase the required ullage volume between the injector and the catalyst bed, which has a negative effect on the thrust-to-weight ratio, as described in the previous study [71].…”

Section: Experimental Test Results and Discussionmentioning

confidence: 99%

Preliminary Assessment of Hydrogen Peroxide Gel as an Oxidizer in a Catalyst Ignited Hybrid Thruster

Huh

Jyoti

Yun

et al. 2018

International Journal of Aerospace Engineering

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In regard to propulsion system applications, the stability of liquid propellants in long-term storage is of increasing importance, and this had led to a greater interest in gelation technology. As part of a preliminary test to determine the feasibility of using a gel propellant in a rocket with a catalyst bed, a hybrid rocket with a catalyst reactor using a gel propellant as an oxidizer was tested for the first time in this study. Experiments were conducted with two different oxidizers: one with liquid phase hydrogen peroxide and the other with gel phase hydrogen peroxide, as well as high-density polyethylene as fuel for a 250 N class hybrid thruster performance test. The thruster was designed with the catalyst ignition system, and a catalyst was manufactured to be inserted into the catalyst reactor to facilitate oxidizer decomposition. While the test result with neat hydrogen peroxide indicated sufficient decomposition efficiency using a manganese dioxide/alumina catalyst and successful autoignition of the fuel via the decomposed product, gel hydrogen peroxide exhibited insufficient decomposition and there were difficulties in operating the thruster as a part of the catalyst was covered in the gelling agent. This preliminary study identifies the potential challenges of using a gel phase oxidizer in a catalyst ignited hybrid thruster and discusses the technical issues that should be addressed in regard to a gel propellant hybrid thruster design with a catalyst reactor.

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Section: Experimental Test Results and Discussionmentioning

confidence: 99%

Preliminary Assessment of Hydrogen Peroxide Gel as an Oxidizer in a Catalyst Ignited Hybrid Thruster

Huh

Jyoti

Yun

et al. 2018

International Journal of Aerospace Engineering

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“…The so-called self-priming sprayer was composed of a nozzle, throat, short diffusion tube, the suction chamber and other components,which could improve atomization and dedusting effect because ambient air can be inhaled when pressure water atomized by a nozzle [8][9], , as shown in Fig. 1.…”

Section: Principle Of Dust Suppressionmentioning

confidence: 99%

Tests on droplets and dust suppression characteristics with self-priming spray magnetization

Ma¹,

Huang²,

Xiong³

et al. 2017

Proceedings of the 2016 International Conference on Engineering and Advanced Technology

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ABSTRACT:To improve the effect of spray and dust reduction, self-priming spray magnetization dedusting was put forward. Moreover, some experiments on droplets and dedusting characteristics were carried out, such as traditional single-nozzle spray, self-priming non-magnetic spray, selfpriming spray with magnets on throat, self-priming spray with magnets on the diffusion tube, and self-priming spray with magnets both on the throat and diffusion tube respectively. The results showed that the SMD value of the self-priming spray was reduced by approximately 12% to 20% and dust reduction efficiency was increased by approximately 5% to 7% compared with the conventional single nozzle, while the SMD value of self-priming spray with magnets was reduced by approximately 10% to 15% and dust reduction efficiency was increased by approximately 6% to 15% compared with the self-priming spray without magnets, the SMD value of self-priming spray with magnets both on the throat and the diffusion tube was less than that of self-priming spray plus magnets on throat or diffusion tube alone, and the dust reduction efficiency was increased by approximately 5%.

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“…Through experiments, a variety of measuring techniques were used to study the atomization characteristics of ejectors. Most of these experiments focused on the macroscopic characteristics of atomization (spray angle, breakup length of liquid film, and droplet size distribution) [22][23][24]. Jia et al [25] measured the spray penetration using a high-speed camera and pointed out that the cone angle increased with pressure.…”

Section: Introductionmentioning

confidence: 99%

Experimental Investigation of the Performance and Spray Characteristics of a Supersonic Two-Phase Flow Ejector with Different Structures

Liu

et al. 2020

Energies

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A two-phase flow ejector is an important part of a water mist fire suppression system, and these devices have become a popular research topic in recent years. This paper proposes a supersonic ejector that aims to improve the efficiency of water mist fire suppression systems. The effects of ejector geometric parameters on the entrainment ratio (ER) were explored. The effects of primary flow pressure (P P ) on the mixing process and flow phenomena were studied by a high-speed camera. The experimental results show that the ER first increases and then decreases with increasing P P . ER increases with increasing ejector area ratio (AR). The P P corresponding to the maximum ER of ejectors with a different nozzle exit position (NXP) is 3.6 bar. The ejector with an NXP of +1 and AR of 6 demonstrate the best performance, and the ER of this ejector reaches 36.29. The spray half-cone angle of the ejector increases with increasing ER, reaching a maximum value of 7.07 • . The unstable atomization half-cone angle is mainly due to a two-phase flow pulsating phenomenon. The pulsation period is 10 ms. In the present study, a general rule that provides a reference for ejector design and selection was obtained through experiments.

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Spray Characteristics of Gelled Propellants in Novel Impinging Jet Injector

Cited by 25 publications

References 16 publications

Preliminary Assessment of Hydrogen Peroxide Gel as an Oxidizer in a Catalyst Ignited Hybrid Thruster

Preliminary Assessment of Hydrogen Peroxide Gel as an Oxidizer in a Catalyst Ignited Hybrid Thruster

Tests on droplets and dust suppression characteristics with self-priming spray magnetization

Experimental Investigation of the Performance and Spray Characteristics of a Supersonic Two-Phase Flow Ejector with Different Structures

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