Study on Size Distribution and Flow Characteristics of Condensed Products in Solid Rocket Motor

The size distribution of condensed products during the combustion of aluminized propellants and flow characteristics of the gas-solid two-phase flow in solid rocket motor were studied in this paper. Firstly, based on the laser scattering technology, an online detection system for condensed products in plume was established, and the size detection of condensed products in the plume of solid rocket motor is carried out. Secondly, a numerical model of two-phase flow in solid rocket motor is established by combining the real size distribution of products in the plume with discrete phase model through the Rosin-Rammler distribution function. Besides, numerical simulation research is carried out under the same experimental conditions, focusing on the influence of condensed products with real size on the characteristics of solid rocket motor. The results show that the innovation measurement system can be used to obtain the size distribution characteristic of condensed products in the plume. At the particle size of stable stage, the mean size, D v 50 , is 104 μm, which is the smallest among all stages. It is also suggested that condensed products at the end stage have the most impact on the flow behavior in solid rocket motor, in that the shock structure, Mach number, and temperature distribution in the near field of plume are significantly changed.

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Unsteady Eulerian two-phase flow analysis of solid rocket motor slag

10.2514/6.1997-2859 ◽

1997 ◽

Cited By ~ 4

Author(s):

Franck Godfroy ◽

Jean-Francois Guery ◽

Franck Godfroy ◽

Jean-Francois Guery

Keyword(s):

Two Phase Flow ◽

Flow Analysis ◽

Rocket Motor ◽

Phase Flow ◽

Solid Rocket Motor ◽

Two Phase ◽

Solid Rocket

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A potential, two-phase flow model for predicting solid rocket motor slag

10.2514/6.1993-2307 ◽

1993 ◽

Author(s):

RANDALL SMITH-KENT ◽

FRED PERKINS ◽

RALPH ABEL

Keyword(s):

Flow Model ◽

Two Phase Flow ◽

Rocket Motor ◽

Phase Flow ◽

Solid Rocket Motor ◽

Two Phase ◽

Solid Rocket

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

Journal of Heat Transfer ◽

10.1115/1.1999652 ◽

2005 ◽

Vol 127 (9) ◽

pp. 1057-1061 ◽

Cited By ~ 17

Author(s):

Yumin Xiao ◽

R. S. Amano ◽

Timin Cai ◽

Jiang Li

Keyword(s):

Boundary Conditions ◽

Combustion Chamber ◽

Solid Propellant ◽

Two Phase Flow ◽

New Method ◽

Phase Flow ◽

Solid Rocket Motor ◽

Two Phase ◽

Solid Rocket ◽

Propellant Surface

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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Study of Two Phase Flow Breakup Behavior for Application to Solid Rocket Motor Nozzle

Volume 1A, Symposia: Advances in Fluids Engineering Education; Turbomachinery Flow Predictions and Optimization; Applications in CFD; Bio-Inspired Fluid Mechanics; Droplet-Surface Interactions; CFD Verification and Validation; Development and Applications of Immersed Boundary Methods; DNS, LES, and Hybrid RANS/LES Methods ◽

10.1115/fedsm2014-21256 ◽

2014 ◽

Cited By ~ 1

Author(s):

Ryo S. Amano ◽

Yi-Hsin Yen ◽

Michael Hamman

Keyword(s):

Probability Distribution ◽

Two Phase Flow ◽

Volume Fraction ◽

Flow Simulation ◽

Rocket Motor ◽

Phase Flow ◽

Straight Channel ◽

Solid Rocket Motor ◽

Two Phase ◽

Molten Droplets

This paper presents a method of characterizing liquid breakup phenomena using a probability distribution flow pattern and compares CFD results of a straight channel two-phase flow using k-ε, SST k-ω and Reynolds Stress Model (RSM). Examination of liquid breakup level is essential for solving erosion phenomenon of solid fuel rocket motor (SRM), due to their use aluminum based solid propellants. During the propellant combustion, the aluminum oxidizes into alumina (Al2O3), which tends to agglomerate into molten droplets under a certain flow conditions. The molten droplets can then impinge on the combustion chamber walls, and flow along the nozzle wall. Such agglomerated aluminum leads to erosive damages to the geometry of de Laval nozzle and reduces the SRM propulsion performance. The volume fraction (VF) contour of the liquid can be used as the raw data for time average flow VF contour of straight channel. The flow shows the probability distribution of two-phase boundary which is mostly controlled by the features of different turbulence models. Those results will be used for future comparison to two-phase flow experiment as model selection reference of SRM two-phase supersonic flow simulation.

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