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49479000.pdf2.28 MB
title液体窒素中のインデューサに発生するキャビテーションの熱力学的効果
Other TitleThermodynamic effect on a cavitating inducer in liquid nitrogen
Author(jpn)吉田 義樹; 菊田 研吾; 長谷川 敏; 島垣 満; 中村 憲明; 徳増 崇
Author(eng)Yoshida, Yoshiki; Kikuta, Kengo; Hasegawa, Satoshi; Shimagaki, Mitsuru; Nakamura, Noriaki; Tokumasu, Takashi
Author Affiliation(jpn)宇宙航空研究開発機構 総合技術研究本部 角田宇宙センター; 宇宙航空研究開発機構; 宇宙航空研究開発機構 総合技術研究本部 角田宇宙センター; 宇宙航空研究開発機構 総合技術研究本部 角田宇宙センター; 科学技術振興機構; 東北大学流体科学研究所
Author Affiliation(eng)Japan Aerospace Exploration Agency Kakuda Space Center, Institute of Aerospace Technology; Japan Aerospace Exploration Agency; Japan Aerospace Exploration Agency Kakuda Space Center, Institute of Aerospace Technology; Japan Aerospace Exploration Agency Kakuda Space Center, Institute of Aerospace Technology; Japan Science and Technology Agency; Institute of Fluid Science, Tohoku University
Issue Date2006-03-31
PublisherJapan Aerospace Exploration Agency (JAXA)
宇宙航空研究開発機構
Publication date2006-03-31
Languagejpn
AbstractFor experimental investigations of the thermodynamic effect on a cavitating inducer, it is necessary to observe the cavitation. However, visualizations of the cavitation are not so easy in cryogenic flow. For this reason, we estimated the cavity region in liquid nitrogen based on measurements of the pressure fluctuation near the blade tip. The degree of the thermodynamic effect was found to increase with the increase of the cavity length of the tip cavitation. The estimated temperature depression caused by vaporization increased rapidly when the cavity length extended over the throat. In addition, the estimated temperature inside the bubble nearly reached the temperature of the triple point when the pump performance deteriorated.
DescriptionJAXA Research and Development Report
宇宙航空研究開発機構研究開発報告
Keywordsinducer; liquid propellant rocket engine; thermodynamic effect; cavitation; liquid nitrogen; cryogenic cooling; cryogenic temperature; critical point; turbopump; インデューサ; 液体燃料ロケットエンジン; 熱力学的効果; キャビテーション; 液体窒素; 極低温冷却; 極低温; 臨界点; ターボポンプ
Document TypeTechnical Report
JAXA Category研究開発報告
ISSN1349-1113
SHI-NOAA0049479000
Report NoJAXA-RR-05-020
URIhttps://repository.exst.jaxa.jp/dspace/handle/a-is/32942


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