Mean Burning Rate Variation in Composite Propellant Combustion Due to Longitudinal Acoustic Oscillations

Kathiravan, B.; C, Senthil Kumar; Rajak, Rajendra; Jayaraman, K.

doi:10.2514/1.b37533

Cited by 8 publications

(2 citation statements)

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“…Moreover, Kathiravan et al. [20] studied the interaction between the propellant flame and acoustic oscillation in a full‐scale rocket engine. The results show that acoustic oscillations affect the dynamics of aluminum particles and agglomeration processes, enhance the heat transfer between the flame and the propellant combustion surface, and change the average combustion velocity.…”

Section: Introductionmentioning

confidence: 99%

“…The results showed that acoustic waves have a great influence on the flow of combustion products, the structure and position of the flame, the shape of the combustion surface, the combustion rate, the flow rate of aluminum particles, and the distribution of agglomerates. Moreover, Kathiravan et al [20] studied the interaction between the propellant flame and acoustic oscillation in a full-scale rocket engine. The results show that acoustic oscillations affect the dynamics of aluminum particles and agglomeration processes, enhance the heat transfer between the flame and the propellant combustion surface, and change the average combustion velocity.…”

Section: Introductionmentioning

confidence: 99%

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Investigating the Acoustic Response Characteristics of a Solid Rocket Motor Combustor in High‐Temperature and High‐Pressure Environments

Chen

Zhang

et al. 2022

Propellants Explo Pyrotec

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With the rapid development of aerospace technologies, coupling of pressure oscillations and unstable combustion in solid rocket motors has become a research hotspot in the past few years. In the present study, an experimental system is designed to investigate high-pressure flows subjected to acoustic excitation. Then cold flow experiments and numerical simulations are carried out with different acoustic excitation frequencies, different background pressures, and different ambient temperatures. The pressure oscillation characteristics and the acoustic response characteristics of the combustion chamber in a high-temperature and high-pressure combustion chamber are analyzed. It is found that the frequency of the pressure oscillation inside the combustion chamber and the output excitation frequency of the signal generator are the same. When the excitation frequency is in the range of 50-200 Hz, the sound pressure amplitude corresponding to each test temperature increases with the increase of the frequency. Moreover, when the background pressure is in the range of 0-0.6 MPa, the sound pressure amplitude increases with the increase of the pressure. Meanwhile, there is no clear correlation between the sound pressure amplitude of the combustion chamber and temperature when the chamber temperature is in the range of 293-363 K. The obtained results from the numerical simulation are consistent with the experimental data and the relative error is less than 5.9 %, which verifies the accuracy of the model. The simulated sound pressure amplitude in the combustion chamber at high temperatures and high pressures is a cubic function of pressure and temperature. The present study is expected to provide an innovative way to investigate pressure oscillations and combustion instability of the propellant in the combustion chamber of solid rocket motors at high temperatures and high pressures.

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Section: Introductionmentioning

confidence: 99%

Section: Introductionmentioning

confidence: 99%