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Study of flow in combustion chamber of solid rocket motor

DOI: 10.1615/ICHMT.2009.TurbulHeatMassTransf.130
4 pages

Ryo S. Amano
Department of Mechanical Engineering, University of Wisconsin-Milwaukee, Milwaukee, Wisconsin, USA

Y. Xiao
Department of Mechanical Engineering, University of Wisconsin-Milwaukee, Wisconsin 53201 Milwaukee, USA

Abstract

In a solid rocket motor (SRM) using aluminized composite solid propellant and submerged nozzle, a two-phase flow needs to be investigated by both experiment and computation. 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. 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 two-phase flows.

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