Numerical Analysis of Controlling Cavitation Instabilities in Tandem Cascades

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Cavitation is an inevitable phenomenon that occurs when improvements such as performance enhancement and weight reduction are made to the turbopump in liquid-propellant rocket engines. Unsteady cavitation may cause oscillations (cavitation instabilities) in the turbopump. Accurate prediction and efficient suppression of cavitation instabilities are important for designing turbopumps. We performed a numerical simulation of the unsteady cavitation in tandem cascades and compared the results with those obtained for a single-stage cascade. The type of cavitation instability could be controlled by changing the front- and rear-blade chord lengths. When the clearance gap between the front and rear blades was located near the cascade throat entrance, rotating-stall conditions could be easily achieved, even at high flow rates. Cavitation surge and super-synchronous and sub-synchronous rotating cavitations were suppressed when the clearance gap was located at 40% of the total chord length. When the clearance gap was located inside the cascade throat, cavitation reached a steady state at the σ value where the cavity length equaled the front-blade length; then, cavitation instabilities and unsteady cavitation were suppressed in the low-σ region. When the clearance gap was located at 80% of the total chord length, cavitation surge was completely suppressed, although rotating cavitation occurred over a larger region.

収録刊行物

  • Transactions of the Japan Society for Aeronautical and Space Sciences

    Transactions of the Japan Society for Aeronautical and Space Sciences 54(184), 137-143, 2011-08-04

    一般社団法人 日本航空宇宙学会

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各種コード

  • NII論文ID(NAID)
    10030274536
  • NII書誌ID(NCID)
    AA0086707X
  • 本文言語コード
    ENG
  • 資料種別
    ART
  • ISSN
    05493811
  • NDL 記事登録ID
    11195522
  • NDL 雑誌分類
    ZN25(科学技術--運輸工学--航空機・ロケット)
  • NDL 請求記号
    Z53-M236
  • データ提供元
    CJP書誌  NDL  J-STAGE 
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