WEKO3
アイテム
{"_buckets": {"deposit": "84a579ff-2d00-4482-be3a-5852852d3a45"}, "_deposit": {"created_by": 1, "id": "37338", "owners": [1], "pid": {"revision_id": 0, "type": "depid", "value": "37338"}, "status": "published"}, "_oai": {"id": "oai:jaxa.repo.nii.ac.jp:00037338", "sets": ["1891", "1915"]}, "author_link": ["480207", "480208", "480206", "480209"], "item_5_alternative_title_2": {"attribute_name": "その他のタイトル(英)", "attribute_value_mlt": [{"subitem_alternative_title": "Aerodynamic characteristics of oscillating turbine cascade in transonic flow"}]}, "item_5_biblio_info_10": {"attribute_name": "書誌情報", "attribute_value_mlt": [{"bibliographicIssueDates": {"bibliographicIssueDate": "1999-02", "bibliographicIssueDateType": "Issued"}, "bibliographicPageEnd": "171", "bibliographicPageStart": "167", "bibliographicVolumeNumber": "41", "bibliographic_titles": [{"bibliographic_title": "航空宇宙技術研究所特別資料"}, {"bibliographic_title": "Special Publication of National Aerospace Laboratory", "bibliographic_titleLang": "en"}]}]}, "item_5_description_14": {"attribute_name": "会議概要(会議名, 開催地, 会期, 主催者等)", "attribute_value_mlt": [{"subitem_description": "航空宇宙技術研究所 24-26 Jun. 1998 東京 日本", "subitem_description_type": "Other"}]}, "item_5_description_15": {"attribute_name": "会議概要(会議名, 開催地, 会期, 主催者等)(英)", "attribute_value_mlt": [{"subitem_description": "National Aerospace Laboratory 24-26 Jun. 1998 Tokyo Japan", "subitem_description_type": "Other"}]}, "item_5_description_16": {"attribute_name": "抄録", "attribute_value_mlt": [{"subitem_description": "遷音速タービン翼列の振動翼まわりの非定常な流れ場を、開発したオイラーコードを用いて数値解析した。本研究の目的は、前の実験で観測されたタービン翼の振動不安定性の機構を解明することである。実験においては、設計点近傍の条件、およびそれから離れた、より低い圧力比を持つ条件における流れのパターンを採用した。非定常空力の測定から、翼振動が不安定であるような翼間位相角の範囲を求めた。この不安定性は設計点近傍で顕著であったが、それから離れた条件では不安定性はおおいに抑制された。設計点近傍では、振動翼の隣接翼からの減衰についての負の影響係数が相互に加算された。他方、設計点から離れた条件下ではその係数は、相互に不安定性を打ち消すようにキャンセルしあった。数値解析の結果は、定性的な観点からは、実験において得られた非定常な流れ場を充分に再現することを証明した。振動不安定性は、設計近傍点における翼弦中央部の強い非定常空力に起因することが分かり、これは翼振動に伴う流路断面積の変化により発生する。設計点から離れた条件において、隣接する翼からの衝撃波が、翼弦中央部の周りに入射する場合には、非定常空力の位相角は衝撃波の上流および下流領域の間で顕著に変化した。これによって振動不安定性は抑制された。", "subitem_description_type": "Abstract"}]}, "item_5_description_17": {"attribute_name": "抄録(英)", "attribute_value_mlt": [{"subitem_description": "The unsteady flow field around an oscillating blade of a transonic turbine cascade was numerically analyzed with a developed Euler code. The aim was to clarify the mechanism of vibration instability of the turbine blades found in the previous experiment. In the experiment, two flow patterns were adopted, one of which had a near-design condition, and the other had an off-design condition with lower pressure ratio. From the measurement of unsteady aerodynamic force, a range of interblade phase angle was found where the blade vibration was unstable. The instability was remarkable in the near-design point, while it was much suppressed in the off-design condition. It was realized that the negative influence coefficients of damping from neighboring blades of the oscillating one were added each other in the near-design condition. In the off-design case, on the other hand, the coefficients were canceled out to abbreviate the instability. The numerical results were verified to well reproduce the unsteady flow fields obtained in the experiment in a qualitative sense. The vibration instability was found to come from the strong unsteady aerodynamic force in the midchord area of a blade, in the near-design point, which was generated by the change of flow channel area due to the blade oscillation. When the shock wave from the adjacent blade impinged around the midchord position in an off-design flow condition, the phase angle of the unsteady force significantly changed between the upstream and the downstream region of the shock. The vibration instability was thereby suppressed.", "subitem_description_type": "Other"}]}, "item_5_description_32": {"attribute_name": "資料番号", "attribute_value_mlt": [{"subitem_description": "資料番号: AA0001958024", "subitem_description_type": "Other"}]}, "item_5_description_33": {"attribute_name": "レポート番号", "attribute_value_mlt": [{"subitem_description": "レポート番号: NAL SP-41", "subitem_description_type": "Other"}]}, "item_5_publisher_8": {"attribute_name": "出版者", "attribute_value_mlt": [{"subitem_publisher": "航空宇宙技術研究所"}]}, "item_5_publisher_9": {"attribute_name": "出版者(英)", "attribute_value_mlt": [{"subitem_publisher": "National Aerospace Laboratory (NAL)"}]}, "item_5_source_id_21": {"attribute_name": "ISSN", "attribute_value_mlt": [{"subitem_source_identifier": "0289-260X", "subitem_source_identifier_type": "ISSN"}]}, "item_5_source_id_24": {"attribute_name": "書誌レコードID", "attribute_value_mlt": [{"subitem_source_identifier": "AN10097345", "subitem_source_identifier_type": "NCID"}]}, "item_5_text_35": {"attribute_name": "JAXAカテゴリ", "attribute_value_mlt": [{"subitem_text_value": "JAXAカテゴリ: 航空宇宙技術研究所"}]}, "item_5_text_36": {"attribute_name": "JAXAカテゴリ2", "attribute_value_mlt": [{"subitem_text_value": "JAXAカテゴリ2: AP"}]}, "item_5_text_43": {"attribute_name": "DSpaceコレクション番号", "attribute_value_mlt": [{"subitem_text_value": "DSpaceコレクション番号: 7"}]}, "item_5_text_6": {"attribute_name": "著者所属", "attribute_value_mlt": [{"subitem_text_value": "航空宇宙技術研究所"}, {"subitem_text_value": "航空宇宙技術研究所"}]}, "item_5_text_7": {"attribute_name": "著者所属(英)", "attribute_value_mlt": [{"subitem_text_language": "en", "subitem_text_value": "National Aerospace Laboratory"}, {"subitem_text_language": "en", "subitem_text_value": "National Aerospace Laboratory"}]}, "item_creator": {"attribute_name": "著者", "attribute_type": "creator", "attribute_value_mlt": [{"creatorNames": [{"creatorName": "青塚, 瑞穂"}], "nameIdentifiers": [{"nameIdentifier": "480206", "nameIdentifierScheme": "WEKO"}]}, {"creatorNames": [{"creatorName": "渡辺, 紀徳"}], "nameIdentifiers": [{"nameIdentifier": "480207", "nameIdentifierScheme": "WEKO"}]}, {"creatorNames": [{"creatorName": "Aotsuka, Mizuho", "creatorNameLang": "en"}], "nameIdentifiers": [{"nameIdentifier": "480208", "nameIdentifierScheme": "WEKO"}]}, {"creatorNames": [{"creatorName": "Watanabe, Toshinori", "creatorNameLang": "en"}], "nameIdentifiers": [{"nameIdentifier": "480209", "nameIdentifierScheme": "WEKO"}]}]}, "item_files": {"attribute_name": "ファイル情報", "attribute_type": "file", "attribute_value_mlt": [{"accessrole": "open_date", "date": [{"dateType": "Available", "dateValue": "2020-02-10"}], "displaytype": "detail", "download_preview_message": "", "file_order": 0, "filename": "nalsp0041024.pdf", "filesize": [{"value": "500.4 kB"}], "format": "application/pdf", "future_date_message": "", "is_thumbnail": false, "licensetype": "license_free", "mimetype": "application/pdf", "size": 500400.0, "url": {"label": "nalsp0041024.pdf", "url": "https://jaxa.repo.nii.ac.jp/record/37338/files/nalsp0041024.pdf"}, "version_id": "74cb59d6-d58f-482e-99a7-82ff1a8a214b"}]}, "item_keyword": {"attribute_name": "キーワード", "attribute_value_mlt": [{"subitem_subject": "衝撃波", "subitem_subject_scheme": "Other"}, {"subitem_subject": "圧力分布", "subitem_subject_scheme": "Other"}, {"subitem_subject": "振動不安定", "subitem_subject_scheme": "Other"}, {"subitem_subject": "流れ場", "subitem_subject_scheme": "Other"}, {"subitem_subject": "数値解析", "subitem_subject_scheme": "Other"}, {"subitem_subject": "遷音速流", "subitem_subject_scheme": "Other"}, {"subitem_subject": "2次元オイラー方程式", "subitem_subject_scheme": "Other"}, {"subitem_subject": "H型格子", "subitem_subject_scheme": "Other"}, {"subitem_subject": "境界条件", "subitem_subject_scheme": "Other"}, {"subitem_subject": "リーマン不変量", "subitem_subject_scheme": "Other"}, {"subitem_subject": "振動翼", "subitem_subject_scheme": "Other"}, {"subitem_subject": "翼間位相角", "subitem_subject_scheme": "Other"}, {"subitem_subject": "shock wave", "subitem_subject_language": "en", "subitem_subject_scheme": "Other"}, {"subitem_subject": "pressure distribution", "subitem_subject_language": "en", "subitem_subject_scheme": "Other"}, {"subitem_subject": "vibration instability", "subitem_subject_language": "en", "subitem_subject_scheme": "Other"}, {"subitem_subject": "flow field", "subitem_subject_language": "en", "subitem_subject_scheme": "Other"}, {"subitem_subject": "numerical analysis", "subitem_subject_language": "en", "subitem_subject_scheme": "Other"}, {"subitem_subject": "transonic flow", "subitem_subject_language": "en", "subitem_subject_scheme": "Other"}, {"subitem_subject": "two dimensional Euler equation", "subitem_subject_language": "en", "subitem_subject_scheme": "Other"}, {"subitem_subject": "H type lattice", "subitem_subject_language": "en", "subitem_subject_scheme": "Other"}, {"subitem_subject": "boundary condition", "subitem_subject_language": "en", "subitem_subject_scheme": "Other"}, {"subitem_subject": "Riemann invariance", "subitem_subject_language": "en", "subitem_subject_scheme": "Other"}, {"subitem_subject": "oscillating blade", "subitem_subject_language": "en", "subitem_subject_scheme": "Other"}, {"subitem_subject": "interblade phase angle", "subitem_subject_language": "en", "subitem_subject_scheme": "Other"}]}, "item_language": {"attribute_name": "言語", "attribute_value_mlt": [{"subitem_language": "jpn"}]}, "item_resource_type": {"attribute_name": "資源タイプ", "attribute_value_mlt": [{"resourcetype": "conference paper", "resourceuri": "http://purl.org/coar/resource_type/c_5794"}]}, "item_title": "遷音速タービン振動翼列の空力特性", "item_titles": {"attribute_name": "タイトル", "attribute_value_mlt": [{"subitem_title": "遷音速タービン振動翼列の空力特性"}]}, "item_type_id": "5", "owner": "1", "path": ["1891", "1915"], "permalink_uri": "https://jaxa.repo.nii.ac.jp/records/37338", "pubdate": {"attribute_name": "公開日", "attribute_value": "2015-03-26"}, "publish_date": "2015-03-26", "publish_status": "0", "recid": "37338", "relation": {}, "relation_version_is_last": true, "title": ["遷音速タービン振動翼列の空力特性"], "weko_shared_id": -1}
遷音速タービン振動翼列の空力特性
https://jaxa.repo.nii.ac.jp/records/37338
https://jaxa.repo.nii.ac.jp/records/373382a6fcdde-4c64-4d91-aa7c-06608e6b49b4
名前 / ファイル | ライセンス | アクション |
---|---|---|
nalsp0041024.pdf (500.4 kB)
|
|
Item type | 会議発表論文 / Conference Paper(1) | |||||
---|---|---|---|---|---|---|
公開日 | 2015-03-26 | |||||
タイトル | ||||||
タイトル | 遷音速タービン振動翼列の空力特性 | |||||
言語 | ||||||
言語 | jpn | |||||
キーワード | ||||||
主題Scheme | Other | |||||
主題 | 衝撃波 | |||||
キーワード | ||||||
主題Scheme | Other | |||||
主題 | 圧力分布 | |||||
キーワード | ||||||
主題Scheme | Other | |||||
主題 | 振動不安定 | |||||
キーワード | ||||||
主題Scheme | Other | |||||
主題 | 流れ場 | |||||
キーワード | ||||||
主題Scheme | Other | |||||
主題 | 数値解析 | |||||
キーワード | ||||||
主題Scheme | Other | |||||
主題 | 遷音速流 | |||||
キーワード | ||||||
主題Scheme | Other | |||||
主題 | 2次元オイラー方程式 | |||||
キーワード | ||||||
主題Scheme | Other | |||||
主題 | H型格子 | |||||
キーワード | ||||||
主題Scheme | Other | |||||
主題 | 境界条件 | |||||
キーワード | ||||||
主題Scheme | Other | |||||
主題 | リーマン不変量 | |||||
キーワード | ||||||
主題Scheme | Other | |||||
主題 | 振動翼 | |||||
キーワード | ||||||
主題Scheme | Other | |||||
主題 | 翼間位相角 | |||||
キーワード | ||||||
言語 | en | |||||
主題Scheme | Other | |||||
主題 | shock wave | |||||
キーワード | ||||||
言語 | en | |||||
主題Scheme | Other | |||||
主題 | pressure distribution | |||||
キーワード | ||||||
言語 | en | |||||
主題Scheme | Other | |||||
主題 | vibration instability | |||||
キーワード | ||||||
言語 | en | |||||
主題Scheme | Other | |||||
主題 | flow field | |||||
キーワード | ||||||
言語 | en | |||||
主題Scheme | Other | |||||
主題 | numerical analysis | |||||
キーワード | ||||||
言語 | en | |||||
主題Scheme | Other | |||||
主題 | transonic flow | |||||
キーワード | ||||||
言語 | en | |||||
主題Scheme | Other | |||||
主題 | two dimensional Euler equation | |||||
キーワード | ||||||
言語 | en | |||||
主題Scheme | Other | |||||
主題 | H type lattice | |||||
キーワード | ||||||
言語 | en | |||||
主題Scheme | Other | |||||
主題 | boundary condition | |||||
キーワード | ||||||
言語 | en | |||||
主題Scheme | Other | |||||
主題 | Riemann invariance | |||||
キーワード | ||||||
言語 | en | |||||
主題Scheme | Other | |||||
主題 | oscillating blade | |||||
キーワード | ||||||
言語 | en | |||||
主題Scheme | Other | |||||
主題 | interblade phase angle | |||||
資源タイプ | ||||||
資源タイプ識別子 | http://purl.org/coar/resource_type/c_5794 | |||||
資源タイプ | conference paper | |||||
その他のタイトル(英) | ||||||
その他のタイトル | Aerodynamic characteristics of oscillating turbine cascade in transonic flow | |||||
著者 |
青塚, 瑞穂
× 青塚, 瑞穂× 渡辺, 紀徳× Aotsuka, Mizuho× Watanabe, Toshinori |
|||||
著者所属 | ||||||
航空宇宙技術研究所 | ||||||
著者所属 | ||||||
航空宇宙技術研究所 | ||||||
著者所属(英) | ||||||
en | ||||||
National Aerospace Laboratory | ||||||
著者所属(英) | ||||||
en | ||||||
National Aerospace Laboratory | ||||||
出版者 | ||||||
出版者 | 航空宇宙技術研究所 | |||||
出版者(英) | ||||||
出版者 | National Aerospace Laboratory (NAL) | |||||
書誌情報 |
航空宇宙技術研究所特別資料 en : Special Publication of National Aerospace Laboratory 巻 41, p. 167-171, 発行日 1999-02 |
|||||
会議概要(会議名, 開催地, 会期, 主催者等) | ||||||
内容記述タイプ | Other | |||||
内容記述 | 航空宇宙技術研究所 24-26 Jun. 1998 東京 日本 | |||||
会議概要(会議名, 開催地, 会期, 主催者等)(英) | ||||||
内容記述タイプ | Other | |||||
内容記述 | National Aerospace Laboratory 24-26 Jun. 1998 Tokyo Japan | |||||
抄録 | ||||||
内容記述タイプ | Abstract | |||||
内容記述 | 遷音速タービン翼列の振動翼まわりの非定常な流れ場を、開発したオイラーコードを用いて数値解析した。本研究の目的は、前の実験で観測されたタービン翼の振動不安定性の機構を解明することである。実験においては、設計点近傍の条件、およびそれから離れた、より低い圧力比を持つ条件における流れのパターンを採用した。非定常空力の測定から、翼振動が不安定であるような翼間位相角の範囲を求めた。この不安定性は設計点近傍で顕著であったが、それから離れた条件では不安定性はおおいに抑制された。設計点近傍では、振動翼の隣接翼からの減衰についての負の影響係数が相互に加算された。他方、設計点から離れた条件下ではその係数は、相互に不安定性を打ち消すようにキャンセルしあった。数値解析の結果は、定性的な観点からは、実験において得られた非定常な流れ場を充分に再現することを証明した。振動不安定性は、設計近傍点における翼弦中央部の強い非定常空力に起因することが分かり、これは翼振動に伴う流路断面積の変化により発生する。設計点から離れた条件において、隣接する翼からの衝撃波が、翼弦中央部の周りに入射する場合には、非定常空力の位相角は衝撃波の上流および下流領域の間で顕著に変化した。これによって振動不安定性は抑制された。 | |||||
抄録(英) | ||||||
内容記述タイプ | Other | |||||
内容記述 | The unsteady flow field around an oscillating blade of a transonic turbine cascade was numerically analyzed with a developed Euler code. The aim was to clarify the mechanism of vibration instability of the turbine blades found in the previous experiment. In the experiment, two flow patterns were adopted, one of which had a near-design condition, and the other had an off-design condition with lower pressure ratio. From the measurement of unsteady aerodynamic force, a range of interblade phase angle was found where the blade vibration was unstable. The instability was remarkable in the near-design point, while it was much suppressed in the off-design condition. It was realized that the negative influence coefficients of damping from neighboring blades of the oscillating one were added each other in the near-design condition. In the off-design case, on the other hand, the coefficients were canceled out to abbreviate the instability. The numerical results were verified to well reproduce the unsteady flow fields obtained in the experiment in a qualitative sense. The vibration instability was found to come from the strong unsteady aerodynamic force in the midchord area of a blade, in the near-design point, which was generated by the change of flow channel area due to the blade oscillation. When the shock wave from the adjacent blade impinged around the midchord position in an off-design flow condition, the phase angle of the unsteady force significantly changed between the upstream and the downstream region of the shock. The vibration instability was thereby suppressed. | |||||
ISSN | ||||||
収録物識別子タイプ | ISSN | |||||
収録物識別子 | 0289-260X | |||||
書誌レコードID | ||||||
収録物識別子タイプ | NCID | |||||
収録物識別子 | AN10097345 | |||||
資料番号 | ||||||
内容記述タイプ | Other | |||||
内容記述 | 資料番号: AA0001958024 | |||||
レポート番号 | ||||||
内容記述タイプ | Other | |||||
内容記述 | レポート番号: NAL SP-41 |