Abstract:Abstract:The high temperature and high pressure supersonic jet is one of the key problems in the design of solid rocket motors. To reduce the jet temperature and noise, cooling water is typically injected into the exhaust plume. Numerical simulations for the gas-liquid multiphase flow field with mixture multiphase model were developed and a series of experiments were carried out. By introducing the energy source terms caused by the vaporization of liquid water into the energy equation, a coupling solution was … Show more
“…All these experimental images and data come from Li et al. 23 The numerical results agreed with the experimental results, indicating that the numerical computational model used in this study is accurate and reliable. Figure 1.Schematic of the experiment system.…”
Section: Theoretical Basis and Verificationsupporting
confidence: 78%
“…The state of the multiphase flow field can be evaluated by solving the three conservation equations for the mixture (continuity equation, momentum equation and energy equation), the volume fraction equation for the secondary phases and the algebraic expressions for the slip velocities. 23,31…”
Section: Theoretical Basis and Verificationmentioning
confidence: 99%
“…Authors’ research group conducted a set of experiments in which water was injected into the rocket motor exhaust jet. 22,23 The same mixture model for multiphase fluid and the Lee’s model for water evaporation were used to simulate experimental results.…”
Section: Theoretical Basis and Verificationmentioning
confidence: 99%
“…22 and Li et al. 23 studied the effect of water injection into a free gas jet through experiments and numerical simulations.…”
This study attempts to determine the effect of and mechanisms for the suppression of the ignition pressure and back-flowing exhaust during a hot launch process in a W-shaped silo, considering the missile movement via dynamic mesh technology. The mixture model for the multiphase and the turbulent model employed were experimentally proved to be accurate and reliable. The numerical results show that the injection of water into a missile exhaust can effectively suppress the ignition overpressure, thereby reducing the time of oscillation and oscillation amplitude, and reducing the maximum pressure at missile bottom from 3.68 × 105 Pa to 2.39 × 105 Pa. In addition, water injection makes the back-flowing exhaust remain at the bottom of the launch duct instead of filling the duct, and it cools the missile bottom, thus leading to a reduction in the maximum temperature from 3000 K to approximately 500 K.
“…All these experimental images and data come from Li et al. 23 The numerical results agreed with the experimental results, indicating that the numerical computational model used in this study is accurate and reliable. Figure 1.Schematic of the experiment system.…”
Section: Theoretical Basis and Verificationsupporting
confidence: 78%
“…The state of the multiphase flow field can be evaluated by solving the three conservation equations for the mixture (continuity equation, momentum equation and energy equation), the volume fraction equation for the secondary phases and the algebraic expressions for the slip velocities. 23,31…”
Section: Theoretical Basis and Verificationmentioning
confidence: 99%
“…Authors’ research group conducted a set of experiments in which water was injected into the rocket motor exhaust jet. 22,23 The same mixture model for multiphase fluid and the Lee’s model for water evaporation were used to simulate experimental results.…”
Section: Theoretical Basis and Verificationmentioning
confidence: 99%
“…22 and Li et al. 23 studied the effect of water injection into a free gas jet through experiments and numerical simulations.…”
This study attempts to determine the effect of and mechanisms for the suppression of the ignition pressure and back-flowing exhaust during a hot launch process in a W-shaped silo, considering the missile movement via dynamic mesh technology. The mixture model for the multiphase and the turbulent model employed were experimentally proved to be accurate and reliable. The numerical results show that the injection of water into a missile exhaust can effectively suppress the ignition overpressure, thereby reducing the time of oscillation and oscillation amplitude, and reducing the maximum pressure at missile bottom from 3.68 × 105 Pa to 2.39 × 105 Pa. In addition, water injection makes the back-flowing exhaust remain at the bottom of the launch duct instead of filling the duct, and it cools the missile bottom, thus leading to a reduction in the maximum temperature from 3000 K to approximately 500 K.
“…While a number of simulation studies have been performed to study water injection into rocket exhaust including work in [3], [4], [12], [22], and [23], experimental studies are scarce and testament to the difficult test conditions. One study to note is by Liwu et al [6] and later by Zhou et al [7] who investigated water injection into the exhaust plume of a solid rocket motor. A spray ring arrangement with 4 nozzles was utilized and measurements of spray structure and plume temperature were obtained using a high-speed camera and an infrared camera.…”
Section: Motivation and Problem Statementmentioning
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