Effects of particle size on two-phase flow loss in aluminized solid rocket motors

Ziyan Li; Ningfei Wang; Baolu Shi; Shipeng Li; Rongjie Yang

doi:10.1016/j.actaastro.2019.03.022

Effects of particle size on two-phase flow loss in aluminized solid rocket motors

Ziyan Li, Ningfei Wang, Baolu Shi^*, Shipeng Li, Rongjie Yang

^*Corresponding author for this work

Beijing Institute of Technology

Research output: Contribution to journal › Article › peer-review

44 Citations (Scopus)

Abstract

This study investigates the two-phase flow loss in aluminized solid rocket motor (SRM) by addressing the effects of particle size. A simplified axisymmetric 2D numerical simulation model is developed to simulate the flow field of the SRM, in which the two-phase flow consists of seeded inert Al ₂ O ₃ particles and burned gas. The numerical model is verified by lab-scale SRM tests. The results show that the numerical simulation predicts SRM performance accurately when quantitatively capture the true particle size. Based on numerical simulations over a broad range of particle diameters, the effects of particle size on the gaseous phase and particle velocity distributions, particulate trajectories, and the thrust coefficient are systematically examined. It is found that with the same mass content of inert particles the two-phase flow loss decreases with increasing particle size.

Original language	English
Pages (from-to)	33-40
Number of pages	8
Journal	Acta Astronautica
Volume	159
DOIs	https://doi.org/10.1016/j.actaastro.2019.03.022
Publication status	Published - Jun 2019

Keywords

Aluminized propellant
Particle size effect
Solid rocket motor
Two-phase flow loss

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10.1016/j.actaastro.2019.03.022

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@article{f3514f1918be4659845a9c45ed4d1139,

title = "Effects of particle size on two-phase flow loss in aluminized solid rocket motors",

abstract = " This study investigates the two-phase flow loss in aluminized solid rocket motor (SRM) by addressing the effects of particle size. A simplified axisymmetric 2D numerical simulation model is developed to simulate the flow field of the SRM, in which the two-phase flow consists of seeded inert Al 2 O 3 particles and burned gas. The numerical model is verified by lab-scale SRM tests. The results show that the numerical simulation predicts SRM performance accurately when quantitatively capture the true particle size. Based on numerical simulations over a broad range of particle diameters, the effects of particle size on the gaseous phase and particle velocity distributions, particulate trajectories, and the thrust coefficient are systematically examined. It is found that with the same mass content of inert particles the two-phase flow loss decreases with increasing particle size.",

keywords = "Aluminized propellant, Particle size effect, Solid rocket motor, Two-phase flow loss",

author = "Ziyan Li and Ningfei Wang and Baolu Shi and Shipeng Li and Rongjie Yang",

note = "Publisher Copyright: {\textcopyright} 2019 IAA",

year = "2019",

month = jun,

doi = "10.1016/j.actaastro.2019.03.022",

language = "English",

volume = "159",

pages = "33--40",

journal = "Acta Astronautica",

issn = "0094-5765",

publisher = "Elsevier Ltd.",

}

TY - JOUR

T1 - Effects of particle size on two-phase flow loss in aluminized solid rocket motors

AU - Li, Ziyan

AU - Wang, Ningfei

AU - Shi, Baolu

AU - Li, Shipeng

AU - Yang, Rongjie

PY - 2019/6

Y1 - 2019/6

N2 - This study investigates the two-phase flow loss in aluminized solid rocket motor (SRM) by addressing the effects of particle size. A simplified axisymmetric 2D numerical simulation model is developed to simulate the flow field of the SRM, in which the two-phase flow consists of seeded inert Al 2 O 3 particles and burned gas. The numerical model is verified by lab-scale SRM tests. The results show that the numerical simulation predicts SRM performance accurately when quantitatively capture the true particle size. Based on numerical simulations over a broad range of particle diameters, the effects of particle size on the gaseous phase and particle velocity distributions, particulate trajectories, and the thrust coefficient are systematically examined. It is found that with the same mass content of inert particles the two-phase flow loss decreases with increasing particle size.

AB - This study investigates the two-phase flow loss in aluminized solid rocket motor (SRM) by addressing the effects of particle size. A simplified axisymmetric 2D numerical simulation model is developed to simulate the flow field of the SRM, in which the two-phase flow consists of seeded inert Al 2 O 3 particles and burned gas. The numerical model is verified by lab-scale SRM tests. The results show that the numerical simulation predicts SRM performance accurately when quantitatively capture the true particle size. Based on numerical simulations over a broad range of particle diameters, the effects of particle size on the gaseous phase and particle velocity distributions, particulate trajectories, and the thrust coefficient are systematically examined. It is found that with the same mass content of inert particles the two-phase flow loss decreases with increasing particle size.

KW - Aluminized propellant

KW - Particle size effect

KW - Solid rocket motor

KW - Two-phase flow loss

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U2 - 10.1016/j.actaastro.2019.03.022

DO - 10.1016/j.actaastro.2019.03.022

M3 - Article

AN - SCOPUS:85063278221

SN - 0094-5765

VL - 159

SP - 33

EP - 40

JO - Acta Astronautica

JF - Acta Astronautica

ER -

Effects of particle size on two-phase flow loss in aluminized solid rocket motors

Abstract

Keywords

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