Numerical Study on Pressure Loss across the Ball Bearingin Rocket Turbopump Coolant Flow

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  • ロケット用ターボポンプ玉軸受の冷却流れ圧力損失に関する研究
  • ロケットヨウ ターボポンプ タマジクウケ ノ レイキャク ナガレ アツリョク ソンシツ ニ カンスル ケンキュウ

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Abstract

In this study, numerical investigation of coolant flow across the angular contact ball bearing in a rocket turbopump was performed to evaluate pressure loss of the bearing. The results show that the pressure loss tendencies against the bearing revolution speed were significantly different between the flow directions. It was mainly caused by the flow separation behind the ball and centrifugal force effect of swirl flow made by bearing revolution. Furthermore, we get a simplified pressure loss model of the bearing and it can approximately estimate the difference of the pressure losses between the flow directions.

Journal

  • Turbomachinery

    Turbomachinery 39 (6), 358-365, 2011

    Turbomachinery Society of Japan

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