Determination of stall and choke limits of a transonic axial flow compressor using the straemline curvature method
Autor(a) principal: | |
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Data de Publicação: | 2010 |
Tipo de documento: | Dissertação |
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=2090 |
Resumo: | The necessity for high performance axial compressors for various applications is shown. The basic theory associated with the study of these machines is presented. A method for calculating the properties of the flow along the compressor is presented. Depending on the design requirements the number of stages is selected and an appropriate shape of the channel studied. Then the compressor blading is made, row-by-row, from the calculation of the flow using a non-viscous flow associated with a loss model that allows, from the known flow at the leading edge, calculate the flow at the trailing edge. The calculations are made on streamlines initially positioned by the criterion of the same area and then repositioned according to the flow calculation in each row until the streamlines do not change their position anymore. Then the boundary-layer on hub and casing walls is evaluated, calculating the blockage coefficients, initially arbitrated. An iterative procedure is done until the blockage coefficients no longer vary. At the end, there are all the dimensions of the compressor and the properties of the flow on the streamlines at the leading and trailing edges of each row. With the geometry fixed and varying the inlet mass flow the maximum mass flow that would result in choke and the minimum one that would result in stall, or even surge, of the compressor can be determined. The computer program was written aiming at being used in a design optimization research. |
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Biblioteca Digital de Teses e Dissertações do ITA |
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Determination of stall and choke limits of a transonic axial flow compressor using the straemline curvature methodTurbinas a gásTurbocompressoresDesempenhoCoeficientes de escoamentoTurbomáquinasMecânica dos fluidosEngenharia mecânicaAbsorvedores de radiaçãoThe necessity for high performance axial compressors for various applications is shown. The basic theory associated with the study of these machines is presented. A method for calculating the properties of the flow along the compressor is presented. Depending on the design requirements the number of stages is selected and an appropriate shape of the channel studied. Then the compressor blading is made, row-by-row, from the calculation of the flow using a non-viscous flow associated with a loss model that allows, from the known flow at the leading edge, calculate the flow at the trailing edge. The calculations are made on streamlines initially positioned by the criterion of the same area and then repositioned according to the flow calculation in each row until the streamlines do not change their position anymore. Then the boundary-layer on hub and casing walls is evaluated, calculating the blockage coefficients, initially arbitrated. An iterative procedure is done until the blockage coefficients no longer vary. At the end, there are all the dimensions of the compressor and the properties of the flow on the streamlines at the leading and trailing edges of each row. With the geometry fixed and varying the inlet mass flow the maximum mass flow that would result in choke and the minimum one that would result in stall, or even surge, of the compressor can be determined. The computer program was written aiming at being used in a design optimization research.Instituto Tecnológico de AeronáuticaJoão Roberto BarbosaJosué Sanches Figueiredo2010-10-27info:eu-repo/semantics/publishedVersioninfo:eu-repo/semantics/masterThesishttp://www.bd.bibl.ita.br/tde_busca/arquivo.php?codArquivo=2090reponame:Biblioteca Digital de Teses e Dissertações do ITAinstname:Instituto Tecnológico de Aeronáuticainstacron:ITAenginfo:eu-repo/semantics/openAccessapplication/pdf2019-02-02T14:03:48Zoai:agregador.ibict.br.BDTD_ITA:oai:ita.br:2090http://oai.bdtd.ibict.br/requestopendoar:null2020-05-28 19:38:10.898Biblioteca Digital de Teses e Dissertações do ITA - Instituto Tecnológico de Aeronáuticatrue |
dc.title.none.fl_str_mv |
Determination of stall and choke limits of a transonic axial flow compressor using the straemline curvature method |
title |
Determination of stall and choke limits of a transonic axial flow compressor using the straemline curvature method |
spellingShingle |
Determination of stall and choke limits of a transonic axial flow compressor using the straemline curvature method Josué Sanches Figueiredo Turbinas a gás Turbocompressores Desempenho Coeficientes de escoamento Turbomáquinas Mecânica dos fluidos Engenharia mecânica Absorvedores de radiação |
title_short |
Determination of stall and choke limits of a transonic axial flow compressor using the straemline curvature method |
title_full |
Determination of stall and choke limits of a transonic axial flow compressor using the straemline curvature method |
title_fullStr |
Determination of stall and choke limits of a transonic axial flow compressor using the straemline curvature method |
title_full_unstemmed |
Determination of stall and choke limits of a transonic axial flow compressor using the straemline curvature method |
title_sort |
Determination of stall and choke limits of a transonic axial flow compressor using the straemline curvature method |
author |
Josué Sanches Figueiredo |
author_facet |
Josué Sanches Figueiredo |
author_role |
author |
dc.contributor.none.fl_str_mv |
João Roberto Barbosa |
dc.contributor.author.fl_str_mv |
Josué Sanches Figueiredo |
dc.subject.por.fl_str_mv |
Turbinas a gás Turbocompressores Desempenho Coeficientes de escoamento Turbomáquinas Mecânica dos fluidos Engenharia mecânica Absorvedores de radiação |
topic |
Turbinas a gás Turbocompressores Desempenho Coeficientes de escoamento Turbomáquinas Mecânica dos fluidos Engenharia mecânica Absorvedores de radiação |
dc.description.none.fl_txt_mv |
The necessity for high performance axial compressors for various applications is shown. The basic theory associated with the study of these machines is presented. A method for calculating the properties of the flow along the compressor is presented. Depending on the design requirements the number of stages is selected and an appropriate shape of the channel studied. Then the compressor blading is made, row-by-row, from the calculation of the flow using a non-viscous flow associated with a loss model that allows, from the known flow at the leading edge, calculate the flow at the trailing edge. The calculations are made on streamlines initially positioned by the criterion of the same area and then repositioned according to the flow calculation in each row until the streamlines do not change their position anymore. Then the boundary-layer on hub and casing walls is evaluated, calculating the blockage coefficients, initially arbitrated. An iterative procedure is done until the blockage coefficients no longer vary. At the end, there are all the dimensions of the compressor and the properties of the flow on the streamlines at the leading and trailing edges of each row. With the geometry fixed and varying the inlet mass flow the maximum mass flow that would result in choke and the minimum one that would result in stall, or even surge, of the compressor can be determined. The computer program was written aiming at being used in a design optimization research. |
description |
The necessity for high performance axial compressors for various applications is shown. The basic theory associated with the study of these machines is presented. A method for calculating the properties of the flow along the compressor is presented. Depending on the design requirements the number of stages is selected and an appropriate shape of the channel studied. Then the compressor blading is made, row-by-row, from the calculation of the flow using a non-viscous flow associated with a loss model that allows, from the known flow at the leading edge, calculate the flow at the trailing edge. The calculations are made on streamlines initially positioned by the criterion of the same area and then repositioned according to the flow calculation in each row until the streamlines do not change their position anymore. Then the boundary-layer on hub and casing walls is evaluated, calculating the blockage coefficients, initially arbitrated. An iterative procedure is done until the blockage coefficients no longer vary. At the end, there are all the dimensions of the compressor and the properties of the flow on the streamlines at the leading and trailing edges of each row. With the geometry fixed and varying the inlet mass flow the maximum mass flow that would result in choke and the minimum one that would result in stall, or even surge, of the compressor can be determined. The computer program was written aiming at being used in a design optimization research. |
publishDate |
2010 |
dc.date.none.fl_str_mv |
2010-10-27 |
dc.type.driver.fl_str_mv |
info:eu-repo/semantics/publishedVersion info:eu-repo/semantics/masterThesis |
status_str |
publishedVersion |
format |
masterThesis |
dc.identifier.uri.fl_str_mv |
http://www.bd.bibl.ita.br/tde_busca/arquivo.php?codArquivo=2090 |
url |
http://www.bd.bibl.ita.br/tde_busca/arquivo.php?codArquivo=2090 |
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 |
Turbinas a gás Turbocompressores Desempenho Coeficientes de escoamento Turbomáquinas Mecânica dos fluidos Engenharia mecânica Absorvedores de radiação |
_version_ |
1706809279254626304 |