Aircraft loads assessment for windmilling sustained engine imbalance condition.
Ano de defesa: | 2005 |
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Autor(a) principal: | |
Orientador(a): | |
Banca de defesa: | |
Tipo de documento: | Dissertação |
Tipo de acesso: | Acesso aberto |
Idioma: | eng |
Instituição de defesa: |
Instituto Tecnológico de Aeronáutica
|
Programa de Pós-Graduação: |
Não Informado pela instituição
|
Departamento: |
Não Informado pela instituição
|
País: |
Não Informado pela instituição
|
Palavras-chave em Português: | |
Link de acesso: | http://www.bd.bibl.ita.br/tde_busca/arquivo.php?codArquivo=163 |
Resumo: | The failure of an aircraft engine fan blade produces an unbalanced rotor condition. Even after the engine is shutdown, the aerodynamic forces may keep the rotors running during the remainder of the flight. This condition can induce significant vibratory loads throughout the airframe that may damage the airframe structure and critical equipments and also affect the crew's ability to sustain a safe flight. This work intends to present a numerical methodology to assess dynamic vibratory loads in a commercial aircraft under windmilling sustained engine imbalance condition, necessary to demonstrate compliance with the current aeronautical design rules. The problem is treated as linear and is formulated in frequency domain. Direct and modal formulations are described. Particular study is made to build up ways to incorporate damping in the system considering different formulations. Some physical effects present in this problem, such as gyroscopic and aerodynamic loads, are also investigated. In order to assess the dynamic loads, an integrated finite element model of aircraft and engine is necessary. Since the aircraft and engine models are usually developed by different groups, which need to exchange them, condensation techniques are extensively used, and some of these techniques are detailed herein. Methods used to improve the accuracy of results obtained in modal formulation are also discussed. Finally, the proposed methods are applied to a mid size commercial jet and the outcomes are analyzed. |
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Biblioteca Digital de Teses e Dissertações do ITA |
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Aircraft loads assessment for windmilling sustained engine imbalance condition.Cargas vibratóriasAuto-rotaçãoAnálise estrutural dinâmicaAnálise numéricaPás de rotoresEngenharia aeronáuticaThe failure of an aircraft engine fan blade produces an unbalanced rotor condition. Even after the engine is shutdown, the aerodynamic forces may keep the rotors running during the remainder of the flight. This condition can induce significant vibratory loads throughout the airframe that may damage the airframe structure and critical equipments and also affect the crew's ability to sustain a safe flight. This work intends to present a numerical methodology to assess dynamic vibratory loads in a commercial aircraft under windmilling sustained engine imbalance condition, necessary to demonstrate compliance with the current aeronautical design rules. The problem is treated as linear and is formulated in frequency domain. Direct and modal formulations are described. Particular study is made to build up ways to incorporate damping in the system considering different formulations. Some physical effects present in this problem, such as gyroscopic and aerodynamic loads, are also investigated. In order to assess the dynamic loads, an integrated finite element model of aircraft and engine is necessary. Since the aircraft and engine models are usually developed by different groups, which need to exchange them, condensation techniques are extensively used, and some of these techniques are detailed herein. Methods used to improve the accuracy of results obtained in modal formulation are also discussed. Finally, the proposed methods are applied to a mid size commercial jet and the outcomes are analyzed.Instituto Tecnológico de AeronáuticaMaher Nasr Bismarck-NasrHugo Marcelo Nunes2005-05-20info:eu-repo/semantics/publishedVersioninfo:eu-repo/semantics/masterThesishttp://www.bd.bibl.ita.br/tde_busca/arquivo.php?codArquivo=163reponame:Biblioteca Digital de Teses e Dissertações do ITAinstname:Instituto Tecnológico de Aeronáuticainstacron:ITAenginfo:eu-repo/semantics/openAccessapplication/pdf2019-02-02T14:01:40Zoai:agregador.ibict.br.BDTD_ITA:oai:ita.br:163http://oai.bdtd.ibict.br/requestopendoar:null2020-05-28 19:32:29.323Biblioteca Digital de Teses e Dissertações do ITA - Instituto Tecnológico de Aeronáuticatrue |
dc.title.none.fl_str_mv |
Aircraft loads assessment for windmilling sustained engine imbalance condition. |
title |
Aircraft loads assessment for windmilling sustained engine imbalance condition. |
spellingShingle |
Aircraft loads assessment for windmilling sustained engine imbalance condition. Hugo Marcelo Nunes Cargas vibratórias Auto-rotação Análise estrutural dinâmica Análise numérica Pás de rotores Engenharia aeronáutica |
title_short |
Aircraft loads assessment for windmilling sustained engine imbalance condition. |
title_full |
Aircraft loads assessment for windmilling sustained engine imbalance condition. |
title_fullStr |
Aircraft loads assessment for windmilling sustained engine imbalance condition. |
title_full_unstemmed |
Aircraft loads assessment for windmilling sustained engine imbalance condition. |
title_sort |
Aircraft loads assessment for windmilling sustained engine imbalance condition. |
author |
Hugo Marcelo Nunes |
author_facet |
Hugo Marcelo Nunes |
author_role |
author |
dc.contributor.none.fl_str_mv |
Maher Nasr Bismarck-Nasr |
dc.contributor.author.fl_str_mv |
Hugo Marcelo Nunes |
dc.subject.por.fl_str_mv |
Cargas vibratórias Auto-rotação Análise estrutural dinâmica Análise numérica Pás de rotores Engenharia aeronáutica |
topic |
Cargas vibratórias Auto-rotação Análise estrutural dinâmica Análise numérica Pás de rotores Engenharia aeronáutica |
dc.description.none.fl_txt_mv |
The failure of an aircraft engine fan blade produces an unbalanced rotor condition. Even after the engine is shutdown, the aerodynamic forces may keep the rotors running during the remainder of the flight. This condition can induce significant vibratory loads throughout the airframe that may damage the airframe structure and critical equipments and also affect the crew's ability to sustain a safe flight. This work intends to present a numerical methodology to assess dynamic vibratory loads in a commercial aircraft under windmilling sustained engine imbalance condition, necessary to demonstrate compliance with the current aeronautical design rules. The problem is treated as linear and is formulated in frequency domain. Direct and modal formulations are described. Particular study is made to build up ways to incorporate damping in the system considering different formulations. Some physical effects present in this problem, such as gyroscopic and aerodynamic loads, are also investigated. In order to assess the dynamic loads, an integrated finite element model of aircraft and engine is necessary. Since the aircraft and engine models are usually developed by different groups, which need to exchange them, condensation techniques are extensively used, and some of these techniques are detailed herein. Methods used to improve the accuracy of results obtained in modal formulation are also discussed. Finally, the proposed methods are applied to a mid size commercial jet and the outcomes are analyzed. |
description |
The failure of an aircraft engine fan blade produces an unbalanced rotor condition. Even after the engine is shutdown, the aerodynamic forces may keep the rotors running during the remainder of the flight. This condition can induce significant vibratory loads throughout the airframe that may damage the airframe structure and critical equipments and also affect the crew's ability to sustain a safe flight. This work intends to present a numerical methodology to assess dynamic vibratory loads in a commercial aircraft under windmilling sustained engine imbalance condition, necessary to demonstrate compliance with the current aeronautical design rules. The problem is treated as linear and is formulated in frequency domain. Direct and modal formulations are described. Particular study is made to build up ways to incorporate damping in the system considering different formulations. Some physical effects present in this problem, such as gyroscopic and aerodynamic loads, are also investigated. In order to assess the dynamic loads, an integrated finite element model of aircraft and engine is necessary. Since the aircraft and engine models are usually developed by different groups, which need to exchange them, condensation techniques are extensively used, and some of these techniques are detailed herein. Methods used to improve the accuracy of results obtained in modal formulation are also discussed. Finally, the proposed methods are applied to a mid size commercial jet and the outcomes are analyzed. |
publishDate |
2005 |
dc.date.none.fl_str_mv |
2005-05-20 |
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=163 |
url |
http://www.bd.bibl.ita.br/tde_busca/arquivo.php?codArquivo=163 |
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 |
Cargas vibratórias Auto-rotação Análise estrutural dinâmica Análise numérica Pás de rotores Engenharia aeronáutica |
_version_ |
1706804985724928000 |