Numerical analysis of AP/HTPB composite propellant combustion under rapid depressurization

Cao, Yanbang; Yu, Ying; Ye, R.

doi:10.1016/j.applthermaleng.2014.09.051

Cited by 25 publications

(16 citation statements)

References 21 publications

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“…Ma [17] et al analyzed the effect of AP content on the combustion characteristics of AP/HTPB by means of micro-numerical simulation. Cao [18] et al simulated the transient decompression of AP/ HTPB, obtained the flame structure and chemical composition distribution of AP/HTPB in the quenching process, and analyzed the influence of out-of-phase blowing effect on AP/HTPB quenching process.…”

Section: Numerical Simulation and Unsteady Combustion Model Of Ap/htpmentioning

confidence: 99%

Numerical Simulation and Unsteady Combustion Model of AP/HTPB Propellant under Depressurization by Rotation

2019

Propellants Explo Pyrotec

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In order to study micro‐scale combustion characteristics of base‐bleed propellant ammonium perchlorate/hydroxyl terminated polybutadiene (AP/HTPB) under rotation condition, a two‐dimensional unsteady rotating combustion model of periodic sandwich model of AP/HTPB was established. In the gas phase, a two‐step overall reaction was used to couple the gas‐solid boundary layer, the rotational momentum was fitted and the numerical simulation comparative analysis under the initial combustion pressure of 0.1 MPa–5 MPa and the rotation velocity of 0–10 800 r min−1 was experimented. The results show that under the conditions of an initial combustion pressure of 3.5 MPa, a depressurization rate of 1000 MPa s−1 and a rotation velocity of 10 200 r min−1, the formation of a narrow diffusion‐controlled chemical reaction zone appears in the initial stage of depressurization. When the combustion pressure drops to about 0.88 MPa, the flame shows dual characteristics: diffusion‐controlled and premixed combustion. When the pressure dropped to 0.1 MPa, the flame is premixed combustion. The steady combustion process at different combustion pressures and different rotational velocities was analyzed numerically. The results show that there is a linear positive correlation between the flame deflection angle and the pressure. When the rotation velocity is lower than 10 000 r min−1, the deflection angle of the gas flame increases linearly with the rotation velocity. However, when the rotation velocity is higher than 10 000 r min−1, the deflection angle and the rotation velocity of the gas flame increase exponentially. The trend of the average Reynolds number of the combustion surface is basically the same as that of the deflection angle of the gas flame. Therefore, the average Reynolds number of the combustion surface can be used to describe the influence of rotation and pressure on the deflection angle of the gas phase flame.

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Section: Numerical Simulation and Unsteady Combustion Model Of Ap/htpmentioning

confidence: 99%

Numerical Simulation and Unsteady Combustion Model of AP/HTPB Propellant under Depressurization by Rotation

2019

Propellants Explo Pyrotec

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“…The model of Cao et al [47] is very similar to that of Ye et al [46] not only in the reaction mechanism but also in the mathematical equation model. In this case, the authors considered a region in which the propellant changes its phase from solid to gas instead of considering a flat surface like it was the case from Ye et al [46].…”

Section: Cao Et Al 2015mentioning

confidence: 70%

“…In that study, they propose a reduced chemical model with 2 steps and another model with 6 steps. In addition, Kohga [51] provides experimental results of burning AP/HTPB composite propellant with and without the use of additives for low and high pressures and AP content from 20% to 80% and his results are afterwards used by Cao et al [47]. Ramakrishna et al [52] modelled the behaviour of sandwich propellant combustion and validate their results against the experimental ones provided by by Price [53] and Price et al [54].…”

Section: Models To Characterise Composite Propellants Combustionmentioning

confidence: 86%

“…In addition to the classic and the complex combustion models, there are several alternatives in the literature based on simplified combustion mechanisms with reduced chemistry kinetics. Among them, the works of Guirao and Williams [43], Knott and Brewster [44], Cai et al [45], Ye et al [46] and Cao et al [47] stand out. The work done by Vo et al [48] needs also to be remarked since they model the problem of combustion of a solid propellant in which the burning surface is moving which will be the case of the present work since the sublimation of solid will lead to a change of the cells from solid to gas phase changing as a results the domains of each two of them.…”

Section: Models To Characterise Composite Propellants Combustionmentioning

confidence: 99%

“…The model proposed by Cao et al [47] and Ye et al [46] considers energy conservation equation for condensed phase and mass, momentum, energy and species governing equations for gas phase which is treated as ideal gas being viscous terms included in momentum conservation equation.…”

Section: Models To Characterise Composite Propellants Combustionmentioning

confidence: 99%

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Modelado de la combustión de propulsantes sólidos

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Investigation of thermal performance in dual‐fuel units

Xue

2022

Energy Science & Engineering

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Numerical studies were carried out to investigate the thermal performance of the muzzle flow with strong shock discontinuities and gas-gas heat transfer mechanism in the base bleed unit (BBU) of an aerodynamic vehicle under the combined effects of muzzle flow and depressurization process. The process was modeled using the Navier-Stokes equations with chemical kinetics and interior ballistic equations. The results show that the muzzle phenomena with large temperature gradients and different wave structures appear after the supersonic vehicle enters into the free-flight stage. The BBU also experiences a strong depressurization process with the release of high-temperature propellant gas at 2200 K. However, the igniter combustion gas at a higher temperature of 3050 K in the BBU develops downstream and upstream repeatedly under the combined effects of the base wave and depressurization process, which makes the energy conversion process in the unit more complicated. With the projectile leaving the control of the muzzle flow, the BBU is full of the igniter combustion gas and the energy in the unit is uniformly distributed gradually. The high-temperature area, at approximately 2750 K, propagates downstream along the axial and radial directions simultaneously until it finally dominates the entire unit. The maximum temperature of the combustion gas acting on the propellant surface is always 2740 K and the maximum heat flux remains approximately 1250 W/cm 2 at later periods.

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Numerical analysis of AP/HTPB composite propellant combustion under rapid depressurization

Cited by 25 publications

References 21 publications

Numerical Simulation and Unsteady Combustion Model of AP/HTPB Propellant under Depressurization by Rotation

Numerical Simulation and Unsteady Combustion Model of AP/HTPB Propellant under Depressurization by Rotation

Modelado de la combustión de propulsantes sólidos

Investigation of thermal performance in dual‐fuel units

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