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In rocket engine turbopump inducers, the occurrence of unstable phenomena such as cavitation surge, rotating cavitation (RC), and attached asymmetric cavitation (AAC) are known. Particularly, in a three-blade inducer, the occurrence of RC and the transition from RC to AAC have been observed in experiment. However, no analytical explanation of the transition from RC to AAC has yet been provided. In this paper, transition phenomenon from RC to AAC is investigated and explained by considering the interaction between the fluid and the rotor systems. A coupled model of the one-dimensional flow path model of the inducer, a rotor model, and a two-dimensional flow model in a cascade was constructed. The transition from RC to AAC was observed and explained when the amplitude of the inducer's synchronous whirling motion increases.

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Dynamical Modeling and Analysis of Fluid-Structure Interaction Phenomena and Bifurcation Occurring in the Inducer of a Turbopump for Rocket Engines

  • 会议论文

  • 发表日期：

    2025年

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  • Tsuyoshi Inoue,
  • Hayate Okawa,
  • Hironori Horiguchi

摘要

In rocket engine turbopump inducers, the occurrence of unstable phenomena such as cavitation surge, rotating cavitation (RC), and attached asymmetric cavitation (AAC) are known. Particularly, in a three-blade inducer, the occurrence of RC and the transition from RC to AAC have been observed in experiment. However, no analytical explanation of the transition from RC to AAC has yet been provided. In this paper, transition phenomenon from RC to AAC is investigated and explained by considering the interaction between the fluid and the rotor systems. A coupled model of the one-dimensional flow path model of the inducer, a rotor model, and a two-dimensional flow model in a cascade was constructed. The transition from RC to AAC was observed and explained when the amplitude of the inducer's synchronous whirling motion increases.