Unsteady combustion of solid propellants

Chung, T. J.; Kim, P. K.

doi:10.1007/bfb0008659

Cited by 13 publications

(2 citation statements)

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“…During oscillatory combustion, the acoustic wave present in the flow field increases the thermal conductivity of the propellant by 10-15 % which in turn increases the propellant surface temperature [32]. At low excited frequencies, there could be a possibility of the energy transfer from acoustics to propellant flame which may enhance the burning rates, as pointed out [8].…”

Section: Full Papermentioning

confidence: 93%

“…The tangential mode of acoustic oscillation also affects the mean burning rates which were reported by Browniee and Marble [7] under high frequency combustion instability conditions, which shows large variation in mean burning rates. Chung and Kim [8] observed that the natural frequency of flame zone always lies between 1 and 100 Hz as peak frequency. This peak frequency of reaction zone encourages the energy transfer between acoustic wave and combustion flame zone likely to occur in low frequency regions leading to combustion instability as observed in experiment and actual flight conditions as well.…”

Section: Introductionmentioning

confidence: 99%

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Oscillatory Pressure Effect on Mean Burning Rates of Solid Propellant Combustion at Low Frequency Conditions

Kathiravan

Rajak

et al. 2019

Propellants Explo Pyrotec

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The investigation on acoustic pressure oscillation effect on the mean burning rate of solid propellant combustion under quasi and unsteady conditions has been carried out at elevated pressures typical of rocket operation. Experiments were conducted in the window bomb test facility to measure mean burning rate for the mean chamber pressure ranging from 1 to 7 MPa. This analysis facilitates current understanding regarding the mean burning rate variation due to the acoustic wave interaction with propellant flame complexes. The present work is focused on low frequency combustion instability and characterization of the long rocket motor configurations. The window bomb is connected with an exclusively designed rotating valve for the generation of acoustic pressure oscillations at selected mean chamber pressures and the corresponding frequency of operations. Two kinds of ammonium perchlorate/hydroxyl terminated poly butadiene (AP/HTPB) based composite propellants, one with aluminium, and the other without aluminium were considered. Experiments were conducted at the excited frequency of 140 Hz with different excited acoustic pressure amplitudes. This experimental setup facility has the provision of visual observation during propellant combustion using optical methods. The performance of the rotating valve was competent over the tested conditions. These studies reveal that the acoustic pressure amplitudes significantly enhance the mean burning rate of the solid propellants. The response of the aluminized propellants to the excited acoustic oscillations was relatively prominent as compared to that of its non‐aluminized counterparts. The results obtained are extremely useful in combustion instability characteristics of large scale rocket motors.

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Section: Full Papermentioning

confidence: 93%

Section: Introductionmentioning

confidence: 99%