Evaporation characteristics of kerosene droplets with dilute concentrations of ligand-protected aluminum nanoparticles at elevated temperatures

Javed, Irfan; Baek, Seung Wook; Waheed, Khalid; Ali, Ghafar; Cho, Sung Oh

doi:10.1016/j.combustflame.2013.07.007

Cited by 108 publications

(45 citation statements)

References 26 publications

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“…Specifically, Javed et al 3 observed a maximum evaporation rate at 0.50 wt % Al suspension in an 800°C environment, and a maximum regression rate at 0.50 wt % MgO was also observed here. However, the burn rate constants observed here are as high as 111.8 mm 2 /s, while the evaporation rate constants reported by Javed et al 3 are as high as 1.1 mm 2 /s.…”

Section: ■ Discussionsupporting

confidence: 83%

Reaction Dynamics of Rocket Propellant with Magnesium Oxide Nanoparticles

Bello

Pantoya²,

Kappagantula

et al. 2015

Energy Fuels

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The combustion behavior of rocket propellant grade 2 (RP-2) was investigated as a function of magnesium oxide (MgO) nanoparticles (i.e., 20 nm diameter) added at varied concentrations. The MgO nanoparticles were surface-treated with a long-chain carboxylic acid to aid their dispersion in RP-2. The fuel droplet regression rate, surface tension, and heat of combustion of RP-2 with MgO nanoparticle additives were measured to characterize combustion behavior. Heat of combustion and surface tension measurements varied negligibly among all samples indicating that calorific output and surface tension are not controlling parameters influencing fuel combustion behavior. However, fuel droplet regression rates were considerably increased by adding 0.5 wt % MgO from 0.225 to 66.16 mm/s, which is an improvement by 2 orders of magnitude. Further analysis showed that MgO particles enhance diffusive heat transfer, which promotes nucleation and disruptive burning throughout the three stages of regression, heating/evaporation (stage 1), combustion of RP-2 (stage 2), and combustion of carboxylic acid dispersant (stage 3), and, thus, lead to improved fuel droplet combustion. ■ INTRODUCTIONPropellants with improved performance are a compelling need for next-generation propulsion systems. The regression rate is an indicator of propellant performance and defines the rate that a liquid droplet surface recedes over the course of its evaporation and combustion in the presence of an ignition source. 1 An approach for improving the regression rate of rocket propellants is to include particulate additives that affect evaporation and burning behavior. Thus, understanding how solid particles influence combustion behavior is key for optimizing the performance of next-generation liquid fuels.Particle additives introduced into liquid fuels can agglomerate and, thus, work best when they are well-dispersed in the liquid. Typically, a dispersant is added to the liquid fuel, which by itself does not significantly alter the regression rate or burn rate constant but improves the dispersion quality of the particles. 2,3 The particle size is also important, and nanoparticles optimize regression far more than their micrometerscale counterparts. 4 Initial experimental work studying solid particle additives in liquid fuels focused on high concentrations of micrometer-size particles added to liquid propellant systems, but there were significant problems associated with them. Micrometer additives often agglomerate during evaporation and combustion of the fuel droplets, resulting in slow droplet regression rates and decreased combustion efficiency. 5 Later research focused on nanoparticle additives with a higher surface area to volume ratio compared to micrometer particles, facilitating more direct contact between the particles and liquid, leading to more complete combustion and higher combustion efficiency. 6,7 Gan and Qiao 4 compared the burning characteristics of ethanol-and n-decane-based fuel droplets with nano-and micrometer-sized aluminum (Al) particles...

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Section: ■ Discussionsupporting

confidence: 83%

Reaction Dynamics of Rocket Propellant with Magnesium Oxide Nanoparticles

Bello

Pantoya²,

Kappagantula

et al. 2015

Energy Fuels

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“…The evaporation of the binary droplet was accompanied with bubble formation and droplet distortion at elevated temperature and low pressure. In the subsequent works, they studied the evaporation characteristics of HAN-based monopropellants, kerosene and heptane with the addition of aluminum nanoparticles using the same experimental apparatus at elevated temperature and atmospheric pressure [22][23][24]. Hashimoto et al [25] investigated the evaporation characteristics of a palm methyl ester (PME) droplet at high temperatures.…”

Section: Introductionmentioning

confidence: 99%

Evaporation characteristics of acetone–butanol–ethanol and diesel blends droplets at high ambient temperatures

Zhang

Han

et al. 2015

Fuel

104

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“…Several materials like B, Al, Mg, Mn, and Fe were used as additives by several researchers [3,5,[9][10][11][12]. In this work silicon is used, which is easily available at low cost.…”

Section: Synthesis and Characterization Of Nanoadditivementioning

confidence: 99%

Impact of nano-silicon fuel additive on combustion, performance and emission of a twin cylinder CI engine

Kumar

Raja

et al. 2018

MATEC Web of Conferences

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Combustion characteristics of a fuel defines its performance and emission characteristics. Enhancement of combustion characteristics is feasible by improvisation of fuel properties. Fuel additives were used for varying fuel properties. The evolution of ‘nano-concept’ develops countless applications in the existing technologies. In this experiment silicon nanoparticles were synthesized by ball milling micron sized silicon particles for 45 hours. The elemental and structural characterizations for the additive material were carried out by EDS, SEM and TEM analysis. Silicon nano additive was mixed in three different weight proportions with diesel to prepare the test fuels. The fuel properties variation with the addition of nano additive were studied. Engine testing was carried out at constant 1200 rpm speed and varying load conditions. Diesel fuel added with 0.5 wt% Si nanoadditive (Si 0.5) showed maximum load carrying ability among the different test fuels. In comparison with diesel at 1200 rpm and 100% load condition, an increase in torque of 5.91% was observed and BTE was increased by 8.93% with a decrease in NOx emission by 27.3%. Variation in the performance and emission characteristics of the fuels were the results of change in heat release rate and combustion timing with the addition of nano additives which could be studied from the combustion characteristic curves.

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Evaporation characteristics of kerosene droplets with dilute concentrations of ligand-protected aluminum nanoparticles at elevated temperatures

Cited by 108 publications

References 26 publications

Reaction Dynamics of Rocket Propellant with Magnesium Oxide Nanoparticles

Reaction Dynamics of Rocket Propellant with Magnesium Oxide Nanoparticles

Evaporation characteristics of acetone–butanol–ethanol and diesel blends droplets at high ambient temperatures

Impact of nano-silicon fuel additive on combustion, performance and emission of a twin cylinder CI engine

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