Investigation of passive control devices to suppress acoustic instability in combustion chambers.
Autor(a) principal: | |
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Data de Publicação: | 2008 |
Tipo de documento: | Tese |
Idioma: | eng |
Título da fonte: | Biblioteca Digital de Teses e Dissertações do ITA |
Texto Completo: | http://www.bd.bibl.ita.br/tde_busca/arquivo.php?codArquivo=590 |
Resumo: | Combustion instability problems have been experienced during nearly every rocket engine development program, characterized by chamber pressure oscillations and high density of energy release in a volume having relatively low losses. Several distinct types of instability and their physical manifestations have been observed, although the frequency and amplitude of these oscillations and their external manifestations normally vary with the type of instability. The most destructive type of instability is referred to as high frequency instability, resonant combustion or acoustic instability, which is usually eliminated by use of passive control, involving installation of baffles, resonators, or some other modification of geometry. The main purpose of this work is the experimental investigation of use of passive control devices (Helmholtz resonators and baffles) to control acoustic instabilities in combustion chambers, because this type of instability occurs in liquid rocket engines, rocket motors and industrial burners. The first step of this research is the acoustic characterization of chamber, thus cold tests were carried out on full-scale chamber model to analyze the effects of resonators. Experimental frequency spectrum data are in excellent agreement with resonant frequencies and damping rate calculated by theoretical model, demonstrating resonators efficiency to reduce the amplitude of Sound Pressure Level at given resonant frequency. Afterwards, hot tests were carried out on burner with and without resonators, identifying the frequency spectrum of acoustic pressure in chamber, which was compared with cold tests (full-scale model) results and theory by correction factors of temperature, density, and viscosity. The experimental data validated the methodology to design resonators useable to control combustion instabilities. |
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Biblioteca Digital de Teses e Dissertações do ITA |
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Investigation of passive control devices to suppress acoustic instability in combustion chambers.Controle de combustãoCâmaras de combustãoEstabilidade de combustãoRessonadores de HelmholtzEstabilidade em freqüênciaMotores foguetes a propelente líquidoEngenharia aeroespacialCombustion instability problems have been experienced during nearly every rocket engine development program, characterized by chamber pressure oscillations and high density of energy release in a volume having relatively low losses. Several distinct types of instability and their physical manifestations have been observed, although the frequency and amplitude of these oscillations and their external manifestations normally vary with the type of instability. The most destructive type of instability is referred to as high frequency instability, resonant combustion or acoustic instability, which is usually eliminated by use of passive control, involving installation of baffles, resonators, or some other modification of geometry. The main purpose of this work is the experimental investigation of use of passive control devices (Helmholtz resonators and baffles) to control acoustic instabilities in combustion chambers, because this type of instability occurs in liquid rocket engines, rocket motors and industrial burners. The first step of this research is the acoustic characterization of chamber, thus cold tests were carried out on full-scale chamber model to analyze the effects of resonators. Experimental frequency spectrum data are in excellent agreement with resonant frequencies and damping rate calculated by theoretical model, demonstrating resonators efficiency to reduce the amplitude of Sound Pressure Level at given resonant frequency. Afterwards, hot tests were carried out on burner with and without resonators, identifying the frequency spectrum of acoustic pressure in chamber, which was compared with cold tests (full-scale model) results and theory by correction factors of temperature, density, and viscosity. The experimental data validated the methodology to design resonators useable to control combustion instabilities.Instituto Tecnológico de AeronáuticaLuiz Carlos Sandoval GóesAlexsander Alexandrovich KozlovAvandelino Santana Junior2008-08-14info:eu-repo/semantics/publishedVersioninfo:eu-repo/semantics/doctoralThesishttp://www.bd.bibl.ita.br/tde_busca/arquivo.php?codArquivo=590reponame:Biblioteca Digital de Teses e Dissertações do ITAinstname:Instituto Tecnológico de Aeronáuticainstacron:ITAenginfo:eu-repo/semantics/openAccessapplication/pdf2019-02-02T14:01:50Zoai:agregador.ibict.br.BDTD_ITA:oai:ita.br:590http://oai.bdtd.ibict.br/requestopendoar:null2020-05-28 19:33:40.824Biblioteca Digital de Teses e Dissertações do ITA - Instituto Tecnológico de Aeronáuticatrue |
dc.title.none.fl_str_mv |
Investigation of passive control devices to suppress acoustic instability in combustion chambers. |
title |
Investigation of passive control devices to suppress acoustic instability in combustion chambers. |
spellingShingle |
Investigation of passive control devices to suppress acoustic instability in combustion chambers. Avandelino Santana Junior Controle de combustão Câmaras de combustão Estabilidade de combustão Ressonadores de Helmholtz Estabilidade em freqüência Motores foguetes a propelente líquido Engenharia aeroespacial |
title_short |
Investigation of passive control devices to suppress acoustic instability in combustion chambers. |
title_full |
Investigation of passive control devices to suppress acoustic instability in combustion chambers. |
title_fullStr |
Investigation of passive control devices to suppress acoustic instability in combustion chambers. |
title_full_unstemmed |
Investigation of passive control devices to suppress acoustic instability in combustion chambers. |
title_sort |
Investigation of passive control devices to suppress acoustic instability in combustion chambers. |
author |
Avandelino Santana Junior |
author_facet |
Avandelino Santana Junior |
author_role |
author |
dc.contributor.none.fl_str_mv |
Luiz Carlos Sandoval Góes Alexsander Alexandrovich Kozlov |
dc.contributor.author.fl_str_mv |
Avandelino Santana Junior |
dc.subject.por.fl_str_mv |
Controle de combustão Câmaras de combustão Estabilidade de combustão Ressonadores de Helmholtz Estabilidade em freqüência Motores foguetes a propelente líquido Engenharia aeroespacial |
topic |
Controle de combustão Câmaras de combustão Estabilidade de combustão Ressonadores de Helmholtz Estabilidade em freqüência Motores foguetes a propelente líquido Engenharia aeroespacial |
dc.description.none.fl_txt_mv |
Combustion instability problems have been experienced during nearly every rocket engine development program, characterized by chamber pressure oscillations and high density of energy release in a volume having relatively low losses. Several distinct types of instability and their physical manifestations have been observed, although the frequency and amplitude of these oscillations and their external manifestations normally vary with the type of instability. The most destructive type of instability is referred to as high frequency instability, resonant combustion or acoustic instability, which is usually eliminated by use of passive control, involving installation of baffles, resonators, or some other modification of geometry. The main purpose of this work is the experimental investigation of use of passive control devices (Helmholtz resonators and baffles) to control acoustic instabilities in combustion chambers, because this type of instability occurs in liquid rocket engines, rocket motors and industrial burners. The first step of this research is the acoustic characterization of chamber, thus cold tests were carried out on full-scale chamber model to analyze the effects of resonators. Experimental frequency spectrum data are in excellent agreement with resonant frequencies and damping rate calculated by theoretical model, demonstrating resonators efficiency to reduce the amplitude of Sound Pressure Level at given resonant frequency. Afterwards, hot tests were carried out on burner with and without resonators, identifying the frequency spectrum of acoustic pressure in chamber, which was compared with cold tests (full-scale model) results and theory by correction factors of temperature, density, and viscosity. The experimental data validated the methodology to design resonators useable to control combustion instabilities. |
description |
Combustion instability problems have been experienced during nearly every rocket engine development program, characterized by chamber pressure oscillations and high density of energy release in a volume having relatively low losses. Several distinct types of instability and their physical manifestations have been observed, although the frequency and amplitude of these oscillations and their external manifestations normally vary with the type of instability. The most destructive type of instability is referred to as high frequency instability, resonant combustion or acoustic instability, which is usually eliminated by use of passive control, involving installation of baffles, resonators, or some other modification of geometry. The main purpose of this work is the experimental investigation of use of passive control devices (Helmholtz resonators and baffles) to control acoustic instabilities in combustion chambers, because this type of instability occurs in liquid rocket engines, rocket motors and industrial burners. The first step of this research is the acoustic characterization of chamber, thus cold tests were carried out on full-scale chamber model to analyze the effects of resonators. Experimental frequency spectrum data are in excellent agreement with resonant frequencies and damping rate calculated by theoretical model, demonstrating resonators efficiency to reduce the amplitude of Sound Pressure Level at given resonant frequency. Afterwards, hot tests were carried out on burner with and without resonators, identifying the frequency spectrum of acoustic pressure in chamber, which was compared with cold tests (full-scale model) results and theory by correction factors of temperature, density, and viscosity. The experimental data validated the methodology to design resonators useable to control combustion instabilities. |
publishDate |
2008 |
dc.date.none.fl_str_mv |
2008-08-14 |
dc.type.driver.fl_str_mv |
info:eu-repo/semantics/publishedVersion info:eu-repo/semantics/doctoralThesis |
status_str |
publishedVersion |
format |
doctoralThesis |
dc.identifier.uri.fl_str_mv |
http://www.bd.bibl.ita.br/tde_busca/arquivo.php?codArquivo=590 |
url |
http://www.bd.bibl.ita.br/tde_busca/arquivo.php?codArquivo=590 |
dc.language.iso.fl_str_mv |
eng |
language |
eng |
dc.rights.driver.fl_str_mv |
info:eu-repo/semantics/openAccess |
eu_rights_str_mv |
openAccess |
dc.format.none.fl_str_mv |
application/pdf |
dc.publisher.none.fl_str_mv |
Instituto Tecnológico de Aeronáutica |
publisher.none.fl_str_mv |
Instituto Tecnológico de Aeronáutica |
dc.source.none.fl_str_mv |
reponame:Biblioteca Digital de Teses e Dissertações do ITA instname:Instituto Tecnológico de Aeronáutica instacron:ITA |
reponame_str |
Biblioteca Digital de Teses e Dissertações do ITA |
collection |
Biblioteca Digital de Teses e Dissertações do ITA |
instname_str |
Instituto Tecnológico de Aeronáutica |
instacron_str |
ITA |
institution |
ITA |
repository.name.fl_str_mv |
Biblioteca Digital de Teses e Dissertações do ITA - Instituto Tecnológico de Aeronáutica |
repository.mail.fl_str_mv |
|
subject_por_txtF_mv |
Controle de combustão Câmaras de combustão Estabilidade de combustão Ressonadores de Helmholtz Estabilidade em freqüência Motores foguetes a propelente líquido Engenharia aeroespacial |
_version_ |
1706809260257574912 |