Investigation of the Flow In Cold Condition at the Exit of a Supersonic Combustor Test Bench
Autor(a) principal: | |
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Data de Publicação: | 2020 |
Outros Autores: | , , |
Tipo de documento: | Artigo |
Idioma: | eng |
Título da fonte: | Journal of Aerospace Technology and Management (Online) |
Texto Completo: | http://old.scielo.br/scielo.php?script=sci_arttext&pid=S2175-91462020000100345 |
Resumo: | ABSTRACT For studies of hypersonic flows and supersonic combustion in ground test facilities, three devices can be used as ram accelerators, shock tunnels and supersonic combustor test benches. These devices can reproduce, on the ground, similar conditions to those in real flight at a certain altitude and speed. In the case of the supersonic combustor test bench (SCTB), it simulates the same flow conditions inside the combustor of a scramjet. The SCTB consists basically of a combustion chamber or vitiated air generator unit, where the air is heated, and a nozzle, where the air is accelerated to the desired test speed. The supersonic combustor to be tested is directly coupled to the nozzle exit of the SCTB. Ultimately, it was necessary to use a transition piece to connect the nozzle to the combustor to be tested, because the nozzle exit has a circular section and the combustor entrance has a rectangular one. This work aims to present the process of characterizing the cold flow along the SCTB of the Institute for Advanced Studies (IEAv) using the schlieren technique. The interference of the transition piece in obtaining the required flow conditions at the exit of the SCTB or the entrance of the combustor was mainly evaluated. |
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Investigation of the Flow In Cold Condition at the Exit of a Supersonic Combustor Test BenchScramjetSupersonic flowGround testing facilitiesSupersonic nozzleSchlieren techniqueABSTRACT For studies of hypersonic flows and supersonic combustion in ground test facilities, three devices can be used as ram accelerators, shock tunnels and supersonic combustor test benches. These devices can reproduce, on the ground, similar conditions to those in real flight at a certain altitude and speed. In the case of the supersonic combustor test bench (SCTB), it simulates the same flow conditions inside the combustor of a scramjet. The SCTB consists basically of a combustion chamber or vitiated air generator unit, where the air is heated, and a nozzle, where the air is accelerated to the desired test speed. The supersonic combustor to be tested is directly coupled to the nozzle exit of the SCTB. Ultimately, it was necessary to use a transition piece to connect the nozzle to the combustor to be tested, because the nozzle exit has a circular section and the combustor entrance has a rectangular one. This work aims to present the process of characterizing the cold flow along the SCTB of the Institute for Advanced Studies (IEAv) using the schlieren technique. The interference of the transition piece in obtaining the required flow conditions at the exit of the SCTB or the entrance of the combustor was mainly evaluated.Departamento de Ciência e Tecnologia Aeroespacial2020-01-01info:eu-repo/semantics/articleinfo:eu-repo/semantics/publishedVersiontext/htmlhttp://old.scielo.br/scielo.php?script=sci_arttext&pid=S2175-91462020000100345Journal of Aerospace Technology and Management v.12 2020reponame:Journal of Aerospace Technology and Management (Online)instname:Departamento de Ciência e Tecnologia Aeroespacial (DCTA)instacron:DCTA10.5028/jatm.v12.1190info:eu-repo/semantics/openAccessGuimarães,Jefte da SilvaLeite,Valéria Serrano Faillace OliveiraCarinhana Junior,DermevalMinucci,Marco Antônio Salaeng2020-10-19T00:00:00Zoai:scielo:S2175-91462020000100345Revistahttp://www.jatm.com.br/ONGhttps://old.scielo.br/oai/scielo-oai.php||secretary@jatm.com.br2175-91461984-9648opendoar:2020-10-19T00:00Journal of Aerospace Technology and Management (Online) - Departamento de Ciência e Tecnologia Aeroespacial (DCTA)false |
dc.title.none.fl_str_mv |
Investigation of the Flow In Cold Condition at the Exit of a Supersonic Combustor Test Bench |
title |
Investigation of the Flow In Cold Condition at the Exit of a Supersonic Combustor Test Bench |
spellingShingle |
Investigation of the Flow In Cold Condition at the Exit of a Supersonic Combustor Test Bench Guimarães,Jefte da Silva Scramjet Supersonic flow Ground testing facilities Supersonic nozzle Schlieren technique |
title_short |
Investigation of the Flow In Cold Condition at the Exit of a Supersonic Combustor Test Bench |
title_full |
Investigation of the Flow In Cold Condition at the Exit of a Supersonic Combustor Test Bench |
title_fullStr |
Investigation of the Flow In Cold Condition at the Exit of a Supersonic Combustor Test Bench |
title_full_unstemmed |
Investigation of the Flow In Cold Condition at the Exit of a Supersonic Combustor Test Bench |
title_sort |
Investigation of the Flow In Cold Condition at the Exit of a Supersonic Combustor Test Bench |
author |
Guimarães,Jefte da Silva |
author_facet |
Guimarães,Jefte da Silva Leite,Valéria Serrano Faillace Oliveira Carinhana Junior,Dermeval Minucci,Marco Antônio Sala |
author_role |
author |
author2 |
Leite,Valéria Serrano Faillace Oliveira Carinhana Junior,Dermeval Minucci,Marco Antônio Sala |
author2_role |
author author author |
dc.contributor.author.fl_str_mv |
Guimarães,Jefte da Silva Leite,Valéria Serrano Faillace Oliveira Carinhana Junior,Dermeval Minucci,Marco Antônio Sala |
dc.subject.por.fl_str_mv |
Scramjet Supersonic flow Ground testing facilities Supersonic nozzle Schlieren technique |
topic |
Scramjet Supersonic flow Ground testing facilities Supersonic nozzle Schlieren technique |
description |
ABSTRACT For studies of hypersonic flows and supersonic combustion in ground test facilities, three devices can be used as ram accelerators, shock tunnels and supersonic combustor test benches. These devices can reproduce, on the ground, similar conditions to those in real flight at a certain altitude and speed. In the case of the supersonic combustor test bench (SCTB), it simulates the same flow conditions inside the combustor of a scramjet. The SCTB consists basically of a combustion chamber or vitiated air generator unit, where the air is heated, and a nozzle, where the air is accelerated to the desired test speed. The supersonic combustor to be tested is directly coupled to the nozzle exit of the SCTB. Ultimately, it was necessary to use a transition piece to connect the nozzle to the combustor to be tested, because the nozzle exit has a circular section and the combustor entrance has a rectangular one. This work aims to present the process of characterizing the cold flow along the SCTB of the Institute for Advanced Studies (IEAv) using the schlieren technique. The interference of the transition piece in obtaining the required flow conditions at the exit of the SCTB or the entrance of the combustor was mainly evaluated. |
publishDate |
2020 |
dc.date.none.fl_str_mv |
2020-01-01 |
dc.type.driver.fl_str_mv |
info:eu-repo/semantics/article |
dc.type.status.fl_str_mv |
info:eu-repo/semantics/publishedVersion |
format |
article |
status_str |
publishedVersion |
dc.identifier.uri.fl_str_mv |
http://old.scielo.br/scielo.php?script=sci_arttext&pid=S2175-91462020000100345 |
url |
http://old.scielo.br/scielo.php?script=sci_arttext&pid=S2175-91462020000100345 |
dc.language.iso.fl_str_mv |
eng |
language |
eng |
dc.relation.none.fl_str_mv |
10.5028/jatm.v12.1190 |
dc.rights.driver.fl_str_mv |
info:eu-repo/semantics/openAccess |
eu_rights_str_mv |
openAccess |
dc.format.none.fl_str_mv |
text/html |
dc.publisher.none.fl_str_mv |
Departamento de Ciência e Tecnologia Aeroespacial |
publisher.none.fl_str_mv |
Departamento de Ciência e Tecnologia Aeroespacial |
dc.source.none.fl_str_mv |
Journal of Aerospace Technology and Management v.12 2020 reponame:Journal of Aerospace Technology and Management (Online) instname:Departamento de Ciência e Tecnologia Aeroespacial (DCTA) instacron:DCTA |
instname_str |
Departamento de Ciência e Tecnologia Aeroespacial (DCTA) |
instacron_str |
DCTA |
institution |
DCTA |
reponame_str |
Journal of Aerospace Technology and Management (Online) |
collection |
Journal of Aerospace Technology and Management (Online) |
repository.name.fl_str_mv |
Journal of Aerospace Technology and Management (Online) - Departamento de Ciência e Tecnologia Aeroespacial (DCTA) |
repository.mail.fl_str_mv |
||secretary@jatm.com.br |
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1754732532333543424 |