Numerical investigation of slag behavior with combustion /evaporation/breakup/VOF models for solid rocket motors

Liaw, Paul; Chen, Yen-Sen; Shang, H. M.; Shih, Ming Chang; Doran, Denise; Steward, Eric

doi:10.2514/6.1995-2726

Cited by 6 publications

(1 citation statement)

References 12 publications

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“…In 1990s, a number of two-phase compressible viscous CFD codes have been developed for modeling internal two-phase flows in a SRM, e.g., Thiokol's SHARP (Golafshani and Loh [7]), SRA's CELMINT (Sabnis et al [17]), and Aerospace's IS (Chang [4]). In mid 1990s, Salita [16], Chauvot et al [6], and Liaw et al [11] focused their research on slag behavior, including combustion, evaporation, and breakup. Their work adds insight to slag accumulation process.…”

Section: Introductionmentioning

confidence: 99%

Aluminized composite solid propellant particle path in the combustion chamber of a solid rocket motor

Xiao¹,

Amano²

2006

WIT Transactions on Engineering Sciences, Vol 52

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In a solid rocket motor (SRM) using aluminized composite solid propellant and a submerged nozzle, a two-phase flow needs to be investigated by both experiment and computation. The boundary conditions for the ejecting particles constrain their trajectories, hence these affect the two-phase flow calculations, and thus significantly affect the evaluation of the slag accumulation. A new method to determine the velocities of particles on the solid propellant surface was developed in the present study, which is based on the RTR (X-ray Real-time Radiography) technique and coupled with the two-phase flow numerical simulation. A method was developed to simulate the particle ejection from the propellant surface. The moving trajectories of metal particles in a firing combustion chamber were measured by using the RTR high-speed motion analyzer. Image processing software was also developed for the RTR images, so the trajectories of particles could be obtained. Numerical simulations with different propellant-surface boundary conditions were performed to calculate particle trajectories. By comparing the two trajectories, an appropriate boundary condition on the propellant surface was referred. The present method can be extended to study the impingement of particles on a wall and other related twophase flows.

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Section: Introductionmentioning

confidence: 99%

Aluminized composite solid propellant particle path in the combustion chamber of a solid rocket motor

Xiao¹,

Amano²

2006

WIT Transactions on Engineering Sciences, Vol 52

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Modeling and simulation of heat pipes: review

Lee,

Rhi,

Kim

2024

J Mech Sci Technol

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New Method to Determine the Velocities of Particles on a Solid Propellant Surface in a Solid Rocket Motor

Xiao

Amano

Cai

et al. 2005

Journal of Heat Transfer

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Use of aluminized composite solid propellants and submerged nozzles are common in solid rocket motors (SRM). Due to the generation of slag, which injects into a combusted gas flow, a two-phase flow pattern is one of the main flow characteristics that need to be investigated in SRM. Validation of two-phase flow modeling in a solid rocket motor combustion chamber is the focus of this research. The particles’ boundary conditions constrain their trajectories, which affect both the two-phase flow calculations, and the evaluation of the slag accumulation. A harsh operation environment in the SRM with high temperatures and high pressure makes the measurement of the internal flow field quite difficult. The open literature includes only a few sets of experimental data that can be used to validate theoretical analyses and numerical calculations for the two-phase flow in a SRM. Therefore, mathematical models that calculate the trajectories of particles may reach different conclusions mainly because of the boundary conditions. A new method to determine the particle velocities on the solid propellant surface is developed in this study, which is based on the x-ray real-time radiography (RTR) technique, and is coupled with the two-phase flow numerical simulation. Other methods imitate the particle ejection from the propellant surface. The RTR high-speed motion analyzer measures the trajectory of the metal particles in a combustion chamber. An image processing software was developed for tracing a slug particle path with the RTR images in the combustion chamber, by which the trajectories of particles were successfully obtained.

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Numerical investigation of slag behavior with combustion /evaporation/breakup/VOF models for solid rocket motors

Cited by 6 publications

References 12 publications

Aluminized composite solid propellant particle path in the combustion chamber of a solid rocket motor

Aluminized composite solid propellant particle path in the combustion chamber of a solid rocket motor

Modeling and simulation of heat pipes: review

New Method to Determine the Velocities of Particles on a Solid Propellant Surface in a Solid Rocket Motor

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