Design Criteria of Turbopump Inducer for Micro Satellite Launcher and Its Verification

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  • 小型軌道投入ロケット用ターボポンプインデューサの設計クライテリアと設計事例検証
  • コガタ キドウ トウニュウ ロケットヨウ ターボポンプインデューサ ノ セッケイ クライテリア ト セッケイ ジレイ ケンショウ

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Abstract

<p>This paper describes how to design turbo-pump inducers for a micro satellite launcher. The authors organized NASA's design criteria (NASA SP series) and some current design studies. To evaluate the design procedures and the design criteria, we designed inducers and conducted performance tests using a cavitation tunnel. As a result of the test, it was confirmed that we successfully developed high performance inducers that caused no severe cavitation instability phenomena, at the design flow coefficients of 0.09 and 0.1.</p>

Journal

  • Turbomachinery

    Turbomachinery 48 (10), 605-615, 2020

    Turbomachinery Society of Japan

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