JAXA Repository / AIREX 未来へ続く、宙(そら)への英知
64906000.pdf1.53 MB
titleキャビテーション噴流法によるロケットポンプ材料の壊食特性の比較
Other TitleComparison of Cavitation Erosion Properties of the Materials Used in Rocket Turbopump by Cavitating Jet Method
Author(jpn)川崎, 聡; 菊田, 研吾; 吉田, 義樹
Author(eng)Kasasaki, Satoshi; Kikuta, Kengo; Yoshida, Yoshiki
Author Affiliation(jpn)宇宙航空研究開発機構宇宙輸送ミッション本部宇宙輸送系推進技術研究開発センター; IHI; 宇宙航空研究開発機構宇宙輸送ミッション本部宇宙輸送系推進技術研究開発センター
Author Affiliation(eng)Space Transportation Propulsion Research and Development Center, Space Transportation Mission Directorate, Japan Aerospace Exploration Agency (JAXA); IHI; Space Transportation Propulsion Research and Development Center, Space Transportation Mission Directorate, Japan Aerospace Exploration Agency (JAXA)
Issue Date2011-02-28
PublisherJapan Aerospace Exploration Agency (JAXA)
宇宙航空研究開発機構
Publication titleJAXA research and development memorandum
宇宙航空研究開発機構研究開発資料
VolumeJAXA-RM-10-017
Publication date2011-02-28
Languagejpn
eng
AbstractTo compare the cavitation erosion properties, the typical materials used in the rocket engine turbopump were tested by cavitating water jet method. Generally, the solid materials of inducer orimpeller have high erosion resistance, but the silver plating used in the inducer liner is much lower one. The addition agents can improve the erosion resistance of silver plating, which was about tentimes higher than normal silver plating. Furthermore, we tried an experiment with cavitating liquid nitrogen jet. The specimen of pure aluminum was slightly damaged by cavitating liquid nitrogen jet after ten minutes test. It indicated possibility of cryogenic cavitation erosion test.
DescriptionOriginal contains color illustrations
形態: カラー図版あり
KeywordsCavitation; Erosion; Rocket; Turbopump; Cavitating Jet; Cryogenic
Document TypeTechnical Report
JAXA Category研究開発資料
ISSN1349-1121
NCIDAA11983593
SHI-NOAA0064906000
Report NoJAXA-RM-10-017
URIhttps://repository.exst.jaxa.jp/dspace/handle/a-is/18662


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