JAXA Repository / AIREX 未来へ続く、宙(そら)への英知
titleロバスト設計手法を用いたターボポンプ用タービンのトーマスフォース低減
Other TitleReduction in Thomas Force of Rocket Turbopump Turbine by Using Robust Design Process
Author(jpn)瀧田, 純也; 内海, 政春; 島垣, 満; 船崎, 健一
Author(eng)Takida, Junya; Uchimi, Masaharu; Shimagaki, Mitsuru; Funazaki, Kenichi
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エンジン研究開発グループ (JAXA); 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エンジン研究開発グループ (JAXA); 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エンジン研究開発グループ (JAXA); 岩手大学工学部
Author Affiliation(eng)Engine System Research and Development Group, Space Transportation Propulsion Research and Development Center, Space Transportation Mission Directorate, Japan Aerospace Exploration Agency (JAXA); Engine System Research and Development Group, Space Transportation Propulsion Research and Development Center, Space Transportation Mission Directorate, Japan Aerospace Exploration Agency (JAXA); Engine System Research and Development Group, Space Transportation Propulsion Research and Development Center, Space Transportation Mission Directorate, Japan Aerospace Exploration Agency (JAXA); Faculty of Engineering, Iwate University
Issue Date2012-02-24
Publisher宇宙航空研究開発機構
Japan Aerospace Exploration Agency (JAXA)
Publication title宇宙航空研究開発機構研究開発資料
JAXA research and development memorandum
VolumeJAXA-RM-11-011
Start page1
End page7
Publication date2012-02-24
Languagejpn
eng
AbstractAn application of robust design process for reduction in Thomas force of rocket turbopump turbines is presented in this paper.Because of its special specification, rocket turbopump turbines are designed as supersonic impulse turbines, and as a result, these blades have higher loading.In such a high loading blade, there is a possibility of rotor vibration problem generated by turbine instability force, that is, "Thomas Force".Actually in the past engine development in Japan, there was the shaft vibration problem due to "Thomas Force".In order to reduce shaft vibrations, it is important to keep "Thomas Force" small.In this paper, the results of parametric design for the existing rocket turbopump turbine by using the robust design process are discussed.
DescriptionPhysical characteristics: Original contains color illustrations
形態: カラー図版あり
KeywordsThomas Force; Robust Design Process; Rocket Turbopump; Supersonic Impulse Turbine
Document TypeTechnical Report
JAXA Category研究開発資料
ISSN1349-1121
NCIDAA11983593
SHI-NOAA0065209000
Report NoJAXA-RM-11-011
URIhttps://repository.exst.jaxa.jp/dspace/handle/a-is/20811


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