超小型ガスタービン用遠心圧縮機の要素試作 Design and Prototyping of Centrifugal Compressor for Ultra Micro Gas Turbine

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In order to investigate the design method of a micro centrifugal compressor, which is the most important component of an ultra micro gas turbine, impellers having the outer diameter of 20mm were manufactured and tested. The impellers were manufactured by a stereolithography method and a machining. The designed corrected rotational speed is N=500,000 rpm. As a result, the impeller made by the machining was chosen for the present study. The impeller was rotated at N=250,000 rpm. The experimental results with the vaned diffusers having two different divergence angles and the vaneless diffuser were compared. It was found that the vaned diffuser attained the higher flow rate than the vaneless diffuser at the maximum pressure ratio. In addition the maximum pressure ratio was higher for the diffuser having a larger diffuser divergence angle at the high flow rate.

収録刊行物

  • ターボ機械 = Turbomachinery  

    ターボ機械 = Turbomachinery 35(1), 57-62, 2007-01-10 

    Turbomachinery Society of Japan

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各種コード

  • NII論文ID(NAID)
    10018478215
  • NII書誌ID(NCID)
    AN00004836
  • 本文言語コード
    JPN
  • 資料種別
    ART
  • ISSN
    03858839
  • NDL 記事登録ID
    8626993
  • NDL 雑誌分類
    ZN15(科学技術--機械工学・工業--流体機械)
  • NDL 請求記号
    Z16-978
  • データ提供元
    CJP書誌  NDL  J-STAGE 
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