Effects of Orifice Geometry on Gelled Propellants Sprayed from Impinging-Jet Injectors

Fu, Qing-fei; Yang, Lijun; Cui, Kun-da; Zhuang, Fengchen

doi:10.2514/1.b35144

Cited by 11 publications

(3 citation statements)

References 29 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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“…Impact of nozzle length is higher at smaller nozzle diameter (Yin et al, 2014). Like Fu et al, (2014), as the length-to-diameter ratio is increased it gets to a point where additional frictional pressure loss causes the Cd to decrease. The effect of length-to-diameter ratio decreases at high Reynolds number, and Cd becomes diameter ratio dependent.…”

Section: Effect Of Geometrical Factors On CDmentioning

confidence: 96%

Discharge coefficient of high viscosity liquids through nozzles

Essien

Archibong-Eso

Lao

2019

Experimental Thermal and Fluid Science

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Experimental investigation on discharge coefficient, Cd, for high viscosity fluid through nozzles was carried out. The viscosity of the fluid used for the test ranged from 350 to 1500 mPa s. The length-to-diameter ratio of the nozzle, / and the ratio of nozzle diameter to pipe diameter ratios were used to investigate the influence of geometry on Cd. Results show a significant dependence of Cd on Re, l/d and β ratio. An empirical correlation on the discharge coefficient was developed based on the data from this study which was also compared with data from other published studies. This correlation, with an R-squared value of 0.9541, was valid for nozzle sizes 10-20 mm and for Re between 1 and 2000. Cd values obtained from experimental data, and those from the empirical correlation were compared, and a mean standard deviation of 0.0231 was obtained.

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“…Yang et al [21] used a modified empirical equation combining the linear instability analysis method to investigate the instability and breakup characteristics of the sheet formed by a gelled propellant impinging jet injector. Fu et al [7] effects of nozzle geometrical characteristics on sheet formation, breakup and atomization for gels from an impinging jet injector.…”

Section: Introductionmentioning

confidence: 99%

Spray of gelled propellants from an impinging-jet injector under different temperatures

Duan

Cui

et al. 2014

Aerospace Science and Technology

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Effects of Orifice Geometry on Gelled Propellants Sprayed from Impinging-Jet Injectors

Cited by 11 publications

References 29 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

Discharge coefficient of high viscosity liquids through nozzles

Spray of gelled propellants from an impinging-jet injector under different temperatures

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