Evaluation of nozzle damping characteristics by a pulsed method

Wanxing Su; Junwei Li; Mi Yan; Bingbing Sun; Ningfei Wang

doi:10.1016/j.egypro.2014.11.1198

Evaluation of nozzle damping characteristics by a pulsed method

Wanxing Su, Junwei Li^*, Mi Yan, Bingbing Sun, Ningfei Wang

^*Corresponding author for this work

School of Aerospace Engineering

Beijing Institute of Technology

Research output: Contribution to journal › Conference article › peer-review

2 Citations (Scopus)

Abstract

A pulsed method is numerically provided in this paper to evaluate the nozzle damping characteristics. In linear consideration of solid rocket motor, the pulsed oscillation pressure will be attenuated in an exponentially way by the nozzle damping. Based on this method, the damping constants of three models with nozzle throat radii of Rt=25mm, Rt=30mm and Rt=35mm are numerically studied. The results show that the first axial acoustic combustion instability is easily excited when a pulse is exerted on the chamber. The pulse intensity and mean chamber pressure have no effect on the nozzle damping characteristics. The factor that can greatly influence the damping constant is the nozzle throat radius. The bigger nozzle throat radius, the greater the nozzle damping effect. The calculated results are consistent well with the theoretical values.

Original language	English
Pages (from-to)	2339-2342
Number of pages	4
Journal	Energy Procedia
Volume	61
DOIs	https://doi.org/10.1016/j.egypro.2014.11.1198
Publication status	Published - 2014
Event	6th International Conference on Applied Energy, ICAE 2014 - Taipei, Taiwan, Province of China Duration: 30 May 2014 → 2 Jun 2014

Keywords

Combustion intability
Nozzle damping
Pulsed method
Solid rocket motor

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10.1016/j.egypro.2014.11.1198

Cite this

@article{6aaeab66f6fa4170a05264dd517288f7,

title = "Evaluation of nozzle damping characteristics by a pulsed method",

abstract = "A pulsed method is numerically provided in this paper to evaluate the nozzle damping characteristics. In linear consideration of solid rocket motor, the pulsed oscillation pressure will be attenuated in an exponentially way by the nozzle damping. Based on this method, the damping constants of three models with nozzle throat radii of Rt=25mm, Rt=30mm and Rt=35mm are numerically studied. The results show that the first axial acoustic combustion instability is easily excited when a pulse is exerted on the chamber. The pulse intensity and mean chamber pressure have no effect on the nozzle damping characteristics. The factor that can greatly influence the damping constant is the nozzle throat radius. The bigger nozzle throat radius, the greater the nozzle damping effect. The calculated results are consistent well with the theoretical values.",

keywords = "Combustion intability, Nozzle damping, Pulsed method, Solid rocket motor",

author = "Wanxing Su and Junwei Li and Mi Yan and Bingbing Sun and Ningfei Wang",

note = "Publisher Copyright: {\textcopyright} 2014 Published by Elsevier Ltd.; 6th International Conference on Applied Energy, ICAE 2014 ; Conference date: 30-05-2014 Through 02-06-2014",

year = "2014",

doi = "10.1016/j.egypro.2014.11.1198",

language = "English",

volume = "61",

pages = "2339--2342",

journal = "Energy Procedia",

issn = "1876-6102",

publisher = "Elsevier B.V.",

}

TY - JOUR

T1 - Evaluation of nozzle damping characteristics by a pulsed method

AU - Su, Wanxing

AU - Li, Junwei

AU - Yan, Mi

AU - Sun, Bingbing

AU - Wang, Ningfei

PY - 2014

Y1 - 2014

N2 - A pulsed method is numerically provided in this paper to evaluate the nozzle damping characteristics. In linear consideration of solid rocket motor, the pulsed oscillation pressure will be attenuated in an exponentially way by the nozzle damping. Based on this method, the damping constants of three models with nozzle throat radii of Rt=25mm, Rt=30mm and Rt=35mm are numerically studied. The results show that the first axial acoustic combustion instability is easily excited when a pulse is exerted on the chamber. The pulse intensity and mean chamber pressure have no effect on the nozzle damping characteristics. The factor that can greatly influence the damping constant is the nozzle throat radius. The bigger nozzle throat radius, the greater the nozzle damping effect. The calculated results are consistent well with the theoretical values.

AB - A pulsed method is numerically provided in this paper to evaluate the nozzle damping characteristics. In linear consideration of solid rocket motor, the pulsed oscillation pressure will be attenuated in an exponentially way by the nozzle damping. Based on this method, the damping constants of three models with nozzle throat radii of Rt=25mm, Rt=30mm and Rt=35mm are numerically studied. The results show that the first axial acoustic combustion instability is easily excited when a pulse is exerted on the chamber. The pulse intensity and mean chamber pressure have no effect on the nozzle damping characteristics. The factor that can greatly influence the damping constant is the nozzle throat radius. The bigger nozzle throat radius, the greater the nozzle damping effect. The calculated results are consistent well with the theoretical values.

KW - Combustion intability

KW - Nozzle damping

KW - Pulsed method

KW - Solid rocket motor

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U2 - 10.1016/j.egypro.2014.11.1198

DO - 10.1016/j.egypro.2014.11.1198

M3 - Conference article

AN - SCOPUS:84922373964

SN - 1876-6102

VL - 61

SP - 2339

EP - 2342

JO - Energy Procedia

JF - Energy Procedia

T2 - 6th International Conference on Applied Energy, ICAE 2014

Y2 - 30 May 2014 through 2 June 2014

ER -

Evaluation of nozzle damping characteristics by a pulsed method

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Keywords

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