{"created":"2023-06-20T15:15:18.812049+00:00","id":45390,"links":{},"metadata":{"_buckets":{"deposit":"d47630a6-9516-446b-9465-afba1f9ce9a0"},"_deposit":{"created_by":1,"id":"45390","owners":[1],"pid":{"revision_id":0,"type":"depid","value":"45390"},"status":"published"},"_oai":{"id":"oai:jaxa.repo.nii.ac.jp:00045390","sets":["1887:1893","1896:1898:1913:1917"]},"author_link":["474524","474529","474525","474528","474527","474526"],"item_3_alternative_title_2":{"attribute_name":"その他のタイトル（英）","attribute_value_mlt":[{"subitem_alternative_title":"An Experimental Study of a Small High-Speed LH2 Pump for Rockets 3rd Report;Fluid dynamic Performance"}]},"item_3_biblio_info_10":{"attribute_name":"書誌情報","attribute_value_mlt":[{"bibliographicIssueDates":{"bibliographicIssueDate":"1991-11","bibliographicIssueDateType":"Issued"},"bibliographicPageStart":"10","bibliographicVolumeNumber":"1131","bibliographic_titles":[{"bibliographic_title":"航空宇宙技術研究所報告"},{"bibliographic_title":"Technical Report of National Aerospace Laboratory TR-1131","bibliographic_titleLang":"en"}]}]},"item_3_description_16":{"attribute_name":"抄録","attribute_value_mlt":[{"subitem_description":"上段ロケットならびに軌道間輸送機(OTV)などに必要となる小型高速液体水素ポンプの技術資料を取得するため,ロケット用小型LH2ポンプの試作研究を行った。前報その1(軸振動抑制対策(1))では,良好な軸振動特性が得られたことを述べ,前報その2(構造基本設計(2))ではポンプ羽根車材料の選定およびその強度,軸推力の調整設計,軸受,軸シールの性能などについて,良好な性能が得られたことを報告した。引き続き第3報としてLH2ポンプの液体水素,液体窒素を用いた一般性能試験と吸込性能試験および羽根車の流力特性計算について述べるものである。実験の結果,LH2ポンプの性能,効率はほぼ予想した値であった。しかし出口案内羽根に高速回転下で性能の低下が見られたが,出口案内羽根の構造改善を行えばさらに数％の性能向上が期待できる。液体水素を用いた吸込性能試験では良好な吸込性能を示した。特にN=50,000rpmの高速回転下でも性能低下をほとんど示すことなく,飽和蒸気圧状態の液体水素を昇圧した。LH2ポンプの性能計算では主として中瀬・妹尾の方法を用いたが,設計流量付近で効率を考慮すれば,液体水素を用いた試験結果とほぼ一致した。","subitem_description_type":"Abstract"}]},"item_3_description_17":{"attribute_name":"抄録（英）","attribute_value_mlt":[{"subitem_description":"A small high-speed rocket engine hydrogen pump was designed, fabricated, and tested at the National Aerospace Laboratory (NAL)/National Space Development Agency (NASDA) turbopump test facilities using liquid nitrogen and liquid hydrogen as the working fluid in order to determine its associated fluid dynamic performance. Both the overall and suction performance are primarily focused on, with the overall performance being fairy good as was expected. However, at high-speed/high pressure conditions(50,000rpm) a clearances occurred between the pump casing and the pump outlet guide vane; thereby resulting in the pump outlet guide vane showing reduced performance than in low speed conditions (30,000 rpm). Design of the pump outlet guide vane is subsequently necessary to improve high-speed pump performance. Prediction of the impeller performance, being base on Senoo and Nakase′s theory, was found to be in good agreement with the experimental results when pump efficiency is taken into consideration. In addition, the inducer showed a smaller required net positive suction head (NPSH) value than the design value, in fact, it could operate even in a two-phase flow condition at the pump inlet.","subitem_description_type":"Other"}]},"item_3_description_32":{"attribute_name":"資料番号","attribute_value_mlt":[{"subitem_description":"資料番号: NALTR1131000","subitem_description_type":"Other"}]},"item_3_description_33":{"attribute_name":"レポート番号","attribute_value_mlt":[{"subitem_description":"レポート番号: NAL TR-1131","subitem_description_type":"Other"}]},"item_3_publisher_8":{"attribute_name":"出版者","attribute_value_mlt":[{"subitem_publisher":"航空宇宙技術研究所"}]},"item_3_publisher_9":{"attribute_name":"出版者（英）","attribute_value_mlt":[{"subitem_publisher":"National Aerospace Laboratory(NAL)"}]},"item_3_source_id_21":{"attribute_name":"ISSN","attribute_value_mlt":[{"subitem_source_identifier":"0389-4010","subitem_source_identifier_type":"ISSN"}]},"item_3_text_6":{"attribute_name":"著者所属","attribute_value_mlt":[{"subitem_text_value":"航空宇宙技術研究所角田支所"},{"subitem_text_value":"航空宇宙技術研究所角田支所"},{"subitem_text_value":"宇宙開発事業団"}]},"item_3_text_7":{"attribute_name":"著者所属（英）","attribute_value_mlt":[{"subitem_text_language":"en","subitem_text_value":"Kakuda Research Center, National Aerospace Laboratory(NAL)"},{"subitem_text_language":"en","subitem_text_value":"Kakuda Research Center, National Aerospace Laboratory(NAL)"},{"subitem_text_language":"en","subitem_text_value":"National Space Development Agency of Japan(NASDA)"}]},"item_creator":{"attribute_name":"著者","attribute_type":"creator","attribute_value_mlt":[{"creatorNames":[{"creatorName":"山田, 仁"}],"nameIdentifiers":[{}]},{"creatorNames":[{"creatorName":"渡辺, 義明"}],"nameIdentifiers":[{}]},{"creatorNames":[{"creatorName":"平田, 邦夫"}],"nameIdentifiers":[{}]},{"creatorNames":[{"creatorName":"YAMADA, Hitoshi","creatorNameLang":"en"}],"nameIdentifiers":[{}]},{"creatorNames":[{"creatorName":"WATANABE, Yoshiaki","creatorNameLang":"en"}],"nameIdentifiers":[{}]},{"creatorNames":[{"creatorName":"HIRATA, Kunio","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":"2020-01-29"}],"displaytype":"detail","filename":"naltr01131.pdf","filesize":[{"value":"1.1 MB"}],"format":"application/pdf","licensetype":"license_note","mimetype":"application/pdf","url":{"label":"naltr01131.pdf","url":"https://jaxa.repo.nii.ac.jp/record/45390/files/naltr01131.pdf"},"version_id":"647beb9d-ee21-48b4-89a8-0b5b55ae860c"}]},"item_keyword":{"attribute_name":"キーワード","attribute_value_mlt":[{"subitem_subject":"liquid hydrogen pump;  inducer;  pump outlet guide vane","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":"technical report","resourceuri":"http://purl.org/coar/resource_type/c_18gh"}]},"item_title":"ロケット用小型LH2ポンプの研究試作(その3)流力性能","item_titles":{"attribute_name":"タイトル","attribute_value_mlt":[{"subitem_title":"ロケット用小型LH2ポンプの研究試作(その3)流力性能"}]},"item_type_id":"3","owner":"1","path":["1893","1917"],"pubdate":{"attribute_name":"公開日","attribute_value":"2015-03-26"},"publish_date":"2015-03-26","publish_status":"0","recid":"45390","relation_version_is_last":true,"title":["ロケット用小型LH2ポンプの研究試作(その3)流力性能"],"weko_creator_id":"1","weko_shared_id":-1},"updated":"2023-06-20T21:40:20.619547+00:00"}