航空学报2025，Vol.46Issue(14)：157-169,13.DOI:10.7527/S1000-6893.2024.31502
大范围变工况诱导轮空化不稳定实验
Experiment on cavitation instability of inducer under wide-range operating conditions
林荣浩 1项乐 1许开富 1高一凡 1朱振海 1李随波1
作者信息
摘要
Abstract
To develop the rocket engine turbo-pump with a wide range of stable operation,the influence of inlet flow coefficient on the dynamic characteristics of a three-blade inducer is examined based on visualization experiment and analysis of corresponding pressure fluctuation characteristics.It is revealed that the inducer blade tip pressure fluctua-tion amplitude increases with the increase of the inlet flow coefficient,and increases first and then decreases with the decrease of the cavitation number.The amplitude of inducer blade tip pressure fluctuation drops further to the non-cavitating condition in the vicinity of cavitation breakdown.Rotating cavitation is observed at 90%-110%design inlet flow coefficient.Additionally,it is clarified that the occurrence range of rotating cavitation extends to high cavitation number at a lower inlet flow coefficient,leading to the problem of operation stability.At 70%-80%Qd,where positive head-to-flow rate curve is caused by cavitation head breakdown,a sub-synchronous azimuthal instability of about 90%shaft frequency is identified as rotating choking,and an axial instability of about 70%shaft frequency as choked surge.关键词
诱导轮/空化/空化不稳定/可视化实验/压力脉动Key words
inducer/cavitation/cavitation instabilities/experimental visualization/pressure fluctuation分类
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林荣浩,项乐,许开富,高一凡,朱振海,李随波..大范围变工况诱导轮空化不稳定实验[J].航空学报,2025,46(14):157-169,13.
