Effect of Aluminized-Grain Design on Slag Accumulation

Hess, Eric; Chen, K.; Acosta, P.; Brent, D.; Fendell, Francis E.

doi:10.2514/3.55646

Cited by 21 publications

(2 citation statements)

References 10 publications

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“…The solid rocket working fluid velocity contour is affected by the multiphase particle motion inside the combustion chamber; resulting in the non-equilibrium effect of exhaust gas limits the performance, as reported by Nayfeh and Saric 4 . Moreover, because of the geometry of the motor, molten alumina agglomerates can form resulting in two-phase flow losses 5,6,7 . These agglomerates lower the propulsive efficiency of the exhaust flow because the agglomerates do not expand in the nozzle and also create a drag force on the flow.…”

Section: Introductionmentioning

confidence: 99%

Study of Alumina Flow in a propulsion Chamber

Amano¹

2015

51st AIAA/SAE/ASEE Joint Propulsion Conference

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To understand liquid breakup mechanism is an important role to improve performance of solid rocket motor (SRM), since we could reduce the erosion mechanism near nozzle throat section from liquid states alumina that is the product after aluminum based solid fuel burns. Protection of the nozzle wall could be achieved by enhance liquid breakup mechanism of the liquid alumina inside combustion chamber before bulky alumina slug erode the nozzle section. This paper presents a study of air and water two-phase straight channel experiment and CFD of Large Eddie Simulation (LES), this work provide a validation information on CFD which will be used to simulate liquid alumina breakup mechanism in the future. The study of CFD validation work is carried out by analyzing high-speed camera image through image processing technic and Welch frequency analysis. This image processing extract the air water free surface position and stored it as surface position history which will be used in Welch frequency analysis. By comaire the result of Welch analysis from experiment and simulaiton will help us to understand the capibility of CFD in liquid breakup study. Nomenclature c p = Specific heat under constant pressure g = Gravity n = n-th species of VOF model p = Pressure px = Pixel T = Temperature t = Time u i = i-th component flow velocities ̃ = resolved-scale (large eddie) component are marked with tilde (~) in LES filter X i = i-th component of body forces x i = i-th coordinate component ′ = Subgrid scale component are marked with prim( ` ) in LES filter Symbols = Volume fraction of VOF model = Viscosity = Density of fluid σ = Surface Tension = LES subgrid scale stress I IntroductionAluminum-based propellants are widely used 1 in a solid rocket motor (SRM) due to its high energy density, easiness to prepare, and store and maintain 2 . When aluminum based propellant combusts, it react with oxidant and oxidized into alumina (Al 2 O 3 ). The alumina is in liquid status in the combustion chamber under the working temperature over 3,200K and pressure over 2.0 × 10 7 Pa. Liquid status alumina formed in combustion chamber tends to agglomerate a Professor, Mechanical Engineering, 115 E. Reindl Way, Glendale WI,53212, Associate Fellow of AIAA b Graduate Student, Mechanical Engineering, 115 E. Reindl Way, Glendale WI,53212, Student Member of AIAA Downloaded by CARLETON UNIVERSITY LIBRARY on August 1, 2015 | http://arc.aiaa.org |

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Section: Introductionmentioning

confidence: 99%

Study of Alumina Flow in a propulsion Chamber

Amano¹

2015

51st AIAA/SAE/ASEE Joint Propulsion Conference

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“…Boraas [1], Haloulakos [8], Hess et al [9], and Meyer [12], conducted extensive modeling of slag accumulation and obtained some useful conclusions. 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]).…”

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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Study of Liquid Breakup Mechanism Through a High-Speed Gas Flow

Amano

Yen

2016

Springer Proceedings in Physics

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Effect of Aluminized-Grain Design on Slag Accumulation

Cited by 21 publications

References 10 publications

Study of Alumina Flow in a propulsion Chamber

Study of Alumina Flow in a propulsion Chamber

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

Study of Liquid Breakup Mechanism Through a High-Speed Gas Flow

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