Numerical simulations based evidence of impingement free sound production during vortex-nozzle interaction in solid rocket motors

Lionel Hirschberg; Steven J. Hulshoff; Thierry Schuller; Christophe F. Schram; Jean Collinet

doi:10.2514/6.2019-2421

Numerical simulations based evidence of impingement free sound production during vortex-nozzle interaction in solid rocket motors

Lionel Hirschberg, Steven J. Hulshoff, Thierry Schuller, Christophe F. Schram, Jean Collinet

Research output: Chapter in Book/Report/Conference proceeding › Conference contribution › Academic › peer-review

1 Citation (Scopus)

Abstract

Dedicated numerical simulations of vortex-nozzle interaction indirect noise in solid rocket motors (SRMs) are presented. It is assumed that the flow in the nozzle and hence the sound radiation is not significantly influenced by the global acoustic oscillation of a SRM. Therefore, the study is limited to the acoustic response of a semi-infinite pipe terminated by a choked nozzle. The nozzle considered here is placed flush in a wall forming a right angle to the walls of the combustion chamber. The study focuses on where sound is produced due to vortex-nozzle interaction. The presented results indicate that sound is produced when the vortex is on its approach to the nozzle, rather than by impingement of the vortex on the nozzle walls.

Original language	English
Title of host publication	25th AIAA/CEAS Aeroacoustics Conference, 2019
Publisher	American Institute of Aeronautics and Astronautics
ISBN (Print)	9781624105883
DOIs	https://doi.org/10.2514/6.2019-2421
Publication status	Published - 2019
Externally published	Yes
Event	25th AIAA/CEAS Aeroacoustics Conference, Aeroacoustics 2019 - Delft University of Technology Aula Conference Centre, Delft, Netherlands Duration: 20 May 2019 → 24 May 2019 Conference number: 25

Conference

Conference	25th AIAA/CEAS Aeroacoustics Conference, Aeroacoustics 2019
Abbreviated title	Aeroacoustics 2019
Country/Territory	Netherlands
City	Delft
Period	20/05/19 → 24/05/19

Keywords

n/a OA procedure

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10.2514/6.2019-2421

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@inproceedings{acdbd7617722498f9ff9872a31876965,

title = "Numerical simulations based evidence of impingement free sound production during vortex-nozzle interaction in solid rocket motors",

abstract = "Dedicated numerical simulations of vortex-nozzle interaction indirect noise in solid rocket motors (SRMs) are presented. It is assumed that the flow in the nozzle and hence the sound radiation is not significantly influenced by the global acoustic oscillation of a SRM. Therefore, the study is limited to the acoustic response of a semi-infinite pipe terminated by a choked nozzle. The nozzle considered here is placed flush in a wall forming a right angle to the walls of the combustion chamber. The study focuses on where sound is produced due to vortex-nozzle interaction. The presented results indicate that sound is produced when the vortex is on its approach to the nozzle, rather than by impingement of the vortex on the nozzle walls.",

keywords = "n/a OA procedure",

author = "Lionel Hirschberg and Hulshoff, {Steven J.} and Thierry Schuller and Schram, {Christophe F.} and Jean Collinet",

note = "Funding Information: This work has been carried out within the framework of a CIFRE grant [CIFRE No. 2015/0938]. Supported by ANRT and ArianeGroup for which the authors are grateful. We specifically acknowledge support offered by Serge Radulovic and Franck Godfroy of ArianeGroup. Publisher Copyright: {\textcopyright} 2019, American Institute of Aeronautics and Astronautics Inc, AIAA. All rights reserved.; 25th AIAA/CEAS Aeroacoustics Conference, Aeroacoustics 2019, Aeroacoustics 2019 ; Conference date: 20-05-2019 Through 24-05-2019",

year = "2019",

doi = "10.2514/6.2019-2421",

language = "English",

isbn = "9781624105883",

booktitle = "25th AIAA/CEAS Aeroacoustics Conference, 2019",

publisher = "American Institute of Aeronautics and Astronautics",

address = "United States",

}

Hirschberg, L, Hulshoff, SJ, Schuller, T, Schram, CF & Collinet, J 2019, Numerical simulations based evidence of impingement free sound production during vortex-nozzle interaction in solid rocket motors. in 25th AIAA/CEAS Aeroacoustics Conference, 2019. American Institute of Aeronautics and Astronautics, 25th AIAA/CEAS Aeroacoustics Conference, Aeroacoustics 2019, Delft, Netherlands, 20/05/19. https://doi.org/10.2514/6.2019-2421

Numerical simulations based evidence of impingement free sound production during vortex-nozzle interaction in solid rocket motors. / Hirschberg, Lionel; Hulshoff, Steven J.; Schuller, Thierry et al.
25th AIAA/CEAS Aeroacoustics Conference, 2019. American Institute of Aeronautics and Astronautics, 2019.

Research output: Chapter in Book/Report/Conference proceeding › Conference contribution › Academic › peer-review

TY - GEN

T1 - Numerical simulations based evidence of impingement free sound production during vortex-nozzle interaction in solid rocket motors

AU - Hirschberg, Lionel

AU - Hulshoff, Steven J.

AU - Schuller, Thierry

AU - Schram, Christophe F.

AU - Collinet, Jean

N1 - Conference code: 25

PY - 2019

Y1 - 2019

N2 - Dedicated numerical simulations of vortex-nozzle interaction indirect noise in solid rocket motors (SRMs) are presented. It is assumed that the flow in the nozzle and hence the sound radiation is not significantly influenced by the global acoustic oscillation of a SRM. Therefore, the study is limited to the acoustic response of a semi-infinite pipe terminated by a choked nozzle. The nozzle considered here is placed flush in a wall forming a right angle to the walls of the combustion chamber. The study focuses on where sound is produced due to vortex-nozzle interaction. The presented results indicate that sound is produced when the vortex is on its approach to the nozzle, rather than by impingement of the vortex on the nozzle walls.

AB - Dedicated numerical simulations of vortex-nozzle interaction indirect noise in solid rocket motors (SRMs) are presented. It is assumed that the flow in the nozzle and hence the sound radiation is not significantly influenced by the global acoustic oscillation of a SRM. Therefore, the study is limited to the acoustic response of a semi-infinite pipe terminated by a choked nozzle. The nozzle considered here is placed flush in a wall forming a right angle to the walls of the combustion chamber. The study focuses on where sound is produced due to vortex-nozzle interaction. The presented results indicate that sound is produced when the vortex is on its approach to the nozzle, rather than by impingement of the vortex on the nozzle walls.

KW - n/a OA procedure

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U2 - 10.2514/6.2019-2421

DO - 10.2514/6.2019-2421

M3 - Conference contribution

AN - SCOPUS:85095979211

SN - 9781624105883

BT - 25th AIAA/CEAS Aeroacoustics Conference, 2019

PB - American Institute of Aeronautics and Astronautics

T2 - 25th AIAA/CEAS Aeroacoustics Conference, Aeroacoustics 2019

Y2 - 20 May 2019 through 24 May 2019

ER -

Numerical simulations based evidence of impingement free sound production during vortex-nozzle interaction in solid rocket motors

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