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航天机主发动机高压燃料涡轮泵容易遇到以破坏性大振幅次同步进动为特征的转子动力不稳定问题。本文从转子动力学角度评述高压燃料涡轮泵的原设计和次同步进动问题的进展。评述了用以解释和改进高压燃料涡轮泵稳定性的模型和分析方法。详细讨论了转子动力学模型的下列因素:
Aerospace main engine high-pressure fuel turbine pump is easy to encounter the destructive large-amplitude sub-synchronous precession of rotor dynamic instability. This paper reviews the progress of the original design and subsynchronous precession of high-pressure fuel turbopumps from the perspective of rotor dynamics. The models and analytical methods used to explain and improve the stability of high pressure fuel turbopumps are reviewed. The following factors of the rotor dynamics model are discussed in detail: