Size Distribution of Particles in Combustion Products of Aluminized Composite Propellant

Jeenu, R.; Pinumalla, Kiran; Deepak, Desh

doi:10.2514/1.43482

Cited by 63 publications

(14 citation statements)

References 16 publications

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“…The particle shape is assumed to be spherical, and also it does not change its shape during the flow. Quench bomb measurements 25 for a wide range of propellants suggest that particle size distributions are bimodal log-normal, with small (smoke) particles of mass-median diameter of roughly 1.5 μm, comprising 70-80 per cent of the particle mass, and the large-particle mode of mass-median diameters ranging from 20-100 μm, comprising only 20-30% of the mass. In the absence of any particle distribution pattern along the propellant geometry of the present motor, a fixed particle diameter is assumed in the present study and its effect is estimated for slag accumulation.…”

Section: Slag Accumulation Prediction Of Solid Rocket Motor For Stratmentioning

confidence: 99%

Slag Prediction in Submerged Rocket Nozzle Through Two-Phase CFD Simulations

Chaturvedi¹,

Kumar²,

Chakraborty³

2015

DSJ

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Section: Slag Accumulation Prediction Of Solid Rocket Motor For Stratmentioning

confidence: 99%

Slag Prediction in Submerged Rocket Nozzle Through Two-Phase CFD Simulations

Chaturvedi¹,

Kumar²,

Chakraborty³

2015

DSJ

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“…The ejected aluminum vapor from the molten aluminum surface forms a diffusion flame with alumina "smoke." Alumina particles, which are the combustion products of aluminum in solid propellants, are known to have a bimodal distribution (Babuk et al, 1999;Jeenu et al, 2010) in fine particles with a *Department of Mechanical Engineering, Saitama Institute of Technology 1690 Fusaiji, Fukaya-shi, Saitama 369-0293, Japan E-mail: apollo-fukuchi@sit.ac.jp diameter of several micrometers and large particles with a diameter of several hundred micrometers (JSME Mechanical Engineers' Handbook 4). The former is derived from the alumina "smoke" and the latter is derived from the "cap" on the surface of the agglomerations.…”

Section: Introductionmentioning

confidence: 99%

Effect of aluminum particle size on agglomeration size and burning rate of composite propellant

Fukuchi

2022

JTST

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An experimental investigation on effects of aluminum particle size on the combustion characteristics of aluminized composite propellant was performed. Reducing the agglomeration size on the burning surface is important to reduce slag in the solid rocket motor and increase the combustion efficiency. Four propellants (HTPB 15 wt%, Al 17 wt%, and AP 68 wt%; AP distribution is trimodal) with the same composition except for different in aluminum particle sizes were examined. Average particle sizes of 30 μm, 10 μm, 5 μm, and 2 μm were considered. Combustion tests were examined with an N 2 -flashed strand burner with two windows. A high-speed imaging technique was used to observe the formation and ejection of agglomerations on the propellant burning surface at the atmospheric pressure. The agglomeration sizes and its distributions were measured. All distributions were monomodal, and the mean and peak diameters of the agglomerations reduced with decreasing diameter of ingredient aluminum particles. The propellant strands were burned at pressures ranging from atmospheric pressure to 5 MPa. The burning rate of propellants were measured on the basis of the movement of the combustion surface acquired by a video camera. The propellant with 2 m aluminum particles showed a smaller agglomeration size and higher burning rate (17% higher at 5 MPa) than did the other propellants. 2 μm aluminum particles seem to be effective for decreasing agglomeration size.

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“…Subsequently, alumina (Al 2 O 3 ) droplets are generated as one of the combustion products of aluminum droplets. These droplets vary in size from submicrometer to a few hundred micrometers [1][2][3]. It is reasonable to expect that such droplets with different sizes will collide with one another when they are accelerated at different rates, which is what tends to occur in rocket nozzles and in complex evolving geometries, such as star grains.…”

Section: Introductionmentioning

confidence: 99%

“…As an important initial parameter for two-phase numerical calculation, the size distribution of droplets in a combustion chamber is understood well [1][2][3]. However, only a few studies on droplet collision in a solid rocket motor have been reported in the literature.…”

Section: Introductionmentioning

confidence: 99%

Numerical Investigation of Head-On Binary Collision of Alumina Droplets

Xia

2015

Journal of Propulsion and Power

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A numerical investigation of the head-on collision of two equal-sized alumina droplets has been conducted. Direct numerical simulations were performed by employing a volume of fluid method for tracking the interface and an adaptive mesh for improving the calculation efficiency. First, simulations of the head-on collision of tetradecane droplets in nitrogen were carried out, and three different outcomes of collision were captured: bouncing, coalescence after substantial deformation, and reflexive separation. These outcomes are in good agreement with the experiments. The numerical critical Weber numbers between the different regimes are also in good agreement with their experimental values. Next, the head-on collision of alumina droplets was investigated at various Weber numbers (1-800) and at one Ohnesorge number (0.1151). In addition to the three outcomes captured earlier, coalescence after a long extension between reflexive separation without satellite and reflexive separation with one satellite is observed. Furthermore, the numerical critical Weber numbers between these distinct regimes were obtained, and the numerical critical Weber number between coalescences after substantial deformation and reflexive separation agrees well with its theoretical value. Finally, collision models of alumina droplets are presented by modifying current droplet collision models.

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Size Distribution of Particles in Combustion Products of Aluminized Composite Propellant

Cited by 63 publications

References 16 publications

Slag Prediction in Submerged Rocket Nozzle Through Two-Phase CFD Simulations

Slag Prediction in Submerged Rocket Nozzle Through Two-Phase CFD Simulations

Effect of aluminum particle size on agglomeration size and burning rate of composite propellant

Numerical Investigation of Head-On Binary Collision of Alumina Droplets

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