{"created":"2023-06-20T15:07:57.813679+00:00","id":37340,"links":{},"metadata":{"_buckets":{"deposit":"7a75e9af-0109-4efd-981d-bd3652f2192d"},"_deposit":{"created_by":1,"id":"37340","owners":[1],"pid":{"revision_id":0,"type":"depid","value":"37340"},"status":"published"},"_oai":{"id":"oai:jaxa.repo.nii.ac.jp:00037340","sets":["1887:1891","1896:1898:1913:1915"]},"author_link":["480224","480220","480225","480219","480218","480221","480223","480222"],"item_5_alternative_title_2":{"attribute_name":"その他のタイトル（英）","attribute_value_mlt":[{"subitem_alternative_title":"Toward numerical simulation of rotating stall inception in compressor rotor: Stall phenomenon induced by breakdown of blade tip leakage vortex"}]},"item_5_biblio_info_10":{"attribute_name":"書誌情報","attribute_value_mlt":[{"bibliographicIssueDates":{"bibliographicIssueDate":"1999-02","bibliographicIssueDateType":"Issued"},"bibliographicPageEnd":"184","bibliographicPageStart":"179","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":"翼先端漏れ渦の崩壊を、中程度の翼負荷を持つ低速の軸流圧縮機翼について調べた。渦崩壊の動翼空力に及ぼす影響をナビエ・ストークススキームによる流れのシミュレーション、および流れの可視化手法を崩壊の同定に用いて検討した。シミュレーションの結果によると、漏れ渦の崩壊は最高圧上昇作動条件よりも低い流量において、回転翼の内部で発生することが示される。崩壊は、よどみ点の存在およびそれに続く気泡様の循環流領域によって特徴づけられる。崩壊の開始に伴って、翼先端漏れ渦に顕著な変化が現れる。すなわち、渦のおおきな拡張および、渦の内部に集中している流れ方向の渦度の消失である。拡張は、先端エッジの上流にまで達するきわめて大きなブロッケージ効果を持つ。集中していた渦度の消滅は、回転翼下流における渦の巻き上がりの消失とケーシングへの圧力の消失をもたらす。翼下流の漏れの流れ場は、崩壊領域の気泡様構造の収縮によってもたらされる外向きの軸流によって支配されている。漏れ渦の崩壊は失速点近傍における翼の作動特性に主要な役割を果たすことが分かる。流量が最高圧上昇点作業条件から減少すると、崩壊域は流れ方向、スパン方向およびピッチ方向に急激に成長する。崩壊の成長はブロッケージをもたらし、急激な損失の増大を招く。これにつれて、崩壊域と翼負圧面の相互作用により、負圧面境界層の3次元的な分離が起こり、失速する。この3次元的な失速は、2次元的な翼の失速と本質的に異なっている。","subitem_description_type":"Abstract"}]},"item_5_description_17":{"attribute_name":"抄録（英）","attribute_value_mlt":[{"subitem_description":"The breakdown of tip leakage vortex has been investigated on a low speed axial compressor rotor with moderate blade loading. Effects of the breakdown on the rotor aerodynamics are elucidated by Navier-Stokes flow simulations and visualization techniques for identifying the breakdown. The simulations show that the leakage vortex breakdown occurs inside the rotor at a lower flow rate than the peak pressure rise operating condition. The breakdown is characterized by the existence of the stagnation point followed by a bubble like recirculation region. The onset of breakdown causes significant changes in the nature of the tip leakage vortex: large expansion of the vortex and disappearance of the streamwise vorticity concentrated in the vortex. The expansion has an extremely large blockage effect extending to the upstream of the leading edge. The disappearance of the concentrated vorticity results in no rolling up of the vortex downstream of the rotor and the disappearance of the pressure through on the casing. The leakage flow field downstream of the rotor is dominated by the outward radial flow resulting from the contraction of the bubble-like structure of the breakdown region. It is found that the leakage vortex breakdown plays a major role in characteristic of rotor performance at near stall conditions. As the flow rate is decreased from the peak pressure rise operating condition, the breakdown region grows rapidly in the streamwise, spanwise and pitchwise directions. The growth of the breakdown causes the blockage and the loss to increase drastically. Then, the interaction of the breakdown region with the blade suction surface gives rise to the three dimensional separation of the suction surface boundary layer, thus leading to a stall. This three dimensional stall is substantially different from a two dimensional blade stall.","subitem_description_type":"Other"}]},"item_5_description_32":{"attribute_name":"資料番号","attribute_value_mlt":[{"subitem_description":"資料番号: AA0001958026","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_6":{"attribute_name":"著者所属","attribute_value_mlt":[{"subitem_text_value":"九州大学 工学部"},{"subitem_text_value":"九州大学 大学院工学研究科"},{"subitem_text_value":"九州電力"},{"subitem_text_value":"九州大学 工学部"}]},"item_5_text_7":{"attribute_name":"著者所属（英）","attribute_value_mlt":[{"subitem_text_language":"en","subitem_text_value":"Kyushu University Faculty of Engineering"},{"subitem_text_language":"en","subitem_text_value":"Kyushu University Graduate School of Engineering"},{"subitem_text_language":"en","subitem_text_value":"Kyushu Electric Power Co Inc"},{"subitem_text_language":"en","subitem_text_value":"Kyushu University Faculty of Engineering"}]},"item_creator":{"attribute_name":"著者","attribute_type":"creator","attribute_value_mlt":[{"creatorNames":[{"creatorName":"古川, 雅人"}],"nameIdentifiers":[{}]},{"creatorNames":[{"creatorName":"才木, 一寿"}],"nameIdentifiers":[{}]},{"creatorNames":[{"creatorName":"山田, 和豊"}],"nameIdentifiers":[{}]},{"creatorNames":[{"creatorName":"井上, 雅弘"}],"nameIdentifiers":[{}]},{"creatorNames":[{"creatorName":"Furukawa, Masato","creatorNameLang":"en"}],"nameIdentifiers":[{}]},{"creatorNames":[{"creatorName":"Saiki, Kazuhisa","creatorNameLang":"en"}],"nameIdentifiers":[{}]},{"creatorNames":[{"creatorName":"Yamada, Kazutoyo","creatorNameLang":"en"}],"nameIdentifiers":[{}]},{"creatorNames":[{"creatorName":"Inoue, Masahiro","creatorNameLang":"en"}],"nameIdentifiers":[{}]}]},"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","filename":"nalsp0041026.pdf","filesize":[{"value":"772.1 kB"}],"format":"application/pdf","licensetype":"license_note","mimetype":"application/pdf","url":{"label":"nalsp0041026.pdf","url":"https://jaxa.repo.nii.ac.jp/record/37340/files/nalsp0041026.pdf"},"version_id":"726332b4-9a6f-406c-8a3d-d596bd66fd40"}]},"item_keyword":{"attribute_name":"キーワード","attribute_value_mlt":[{"subitem_subject":"圧縮機動翼","subitem_subject_scheme":"Other"},{"subitem_subject":"失速","subitem_subject_scheme":"Other"},{"subitem_subject":"有限体積法","subitem_subject_scheme":"Other"},{"subitem_subject":"臨界点理論","subitem_subject_scheme":"Other"},{"subitem_subject":"渦コア","subitem_subject_scheme":"Other"},{"subitem_subject":"翼先端漏れ渦","subitem_subject_scheme":"Other"},{"subitem_subject":"渦度","subitem_subject_scheme":"Other"},{"subitem_subject":"ナビエ・ストークス流れ","subitem_subject_scheme":"Other"},{"subitem_subject":"可視化","subitem_subject_scheme":"Other"},{"subitem_subject":"ブロッケージ効果","subitem_subject_scheme":"Other"},{"subitem_subject":"境界層","subitem_subject_scheme":"Other"},{"subitem_subject":"剥離","subitem_subject_scheme":"Other"},{"subitem_subject":"compressor rotor","subitem_subject_language":"en","subitem_subject_scheme":"Other"},{"subitem_subject":"stall","subitem_subject_language":"en","subitem_subject_scheme":"Other"},{"subitem_subject":"finite volume method","subitem_subject_language":"en","subitem_subject_scheme":"Other"},{"subitem_subject":"stagnation point","subitem_subject_language":"en","subitem_subject_scheme":"Other"},{"subitem_subject":"vortex core","subitem_subject_language":"en","subitem_subject_scheme":"Other"},{"subitem_subject":"blade tip leakage vortex","subitem_subject_language":"en","subitem_subject_scheme":"Other"},{"subitem_subject":"vorticity","subitem_subject_language":"en","subitem_subject_scheme":"Other"},{"subitem_subject":"Navier Stokes flow","subitem_subject_language":"en","subitem_subject_scheme":"Other"},{"subitem_subject":"visualization","subitem_subject_language":"en","subitem_subject_scheme":"Other"},{"subitem_subject":"blockage effect","subitem_subject_language":"en","subitem_subject_scheme":"Other"},{"subitem_subject":"boundary layer","subitem_subject_language":"en","subitem_subject_scheme":"Other"},{"subitem_subject":"separation","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 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