Experimental investigation of cavitation instabilities in inducer with different tip clearances  

作　　者：Le XIANG Yonghua TAN Hui CHEN Kaifu XU 

机构地区：[1]Science and Technology on Liquid Rocket Engine Laboratory,Xi’an 710100,China [2]Academy of Aerospace Propulsion Technology,Xi’an 710100,China [3]Xi'an Aerospace Propulsion Institute,Xi’an 710100,China

出　　处：《Chinese Journal of Aeronautics》2021年第9期168-177,共10页中国航空学报（英文版）

基　　金：supported by the National Basic Research Program of China(No.613321)。

摘　　要：To investigate the effect of tip clearance size on cavitation characteristics in a turbopump inducer,a series of experiments have been conducted in a newly developed visualization test facility using room temperature water as working fluid.The pressure fluctuations near the tip region were collected,and the cavity structures under various conditions were documented by a high-speed camera.It is found that large tip clearance distinctly reduces both the non-cavitation and cavitation performance.Three cavitation instabilities,super-synchronous rotating cavitation,synchronous rotating cavitation and cavitation surge have been carefully identified through combination of cross-correlation analysis of pressure signals and visualization results.Large tip clearance displays a remarkable stabilization effect on pressure fluctuation,cavitation surge totally disappears,and the range of occurrence of synchronous rotating cavitation becomes smaller for the large tip clearance,whereas super-synchronous rotating cavitation only occurs in the large tip clearance.The cavitation areas are smaller at large tip clearance,while the flow channels are more seriously choked when cavitation occurs heavily in comparison with those at small tip clearance,which may be responsible for the worse cavitation performance.

关 键 词：Cavitation instabilities INDUCER Pressure fluctuation Tip clearance VISUALIZATION 

分 类 号：V433.9[航空宇航科学与技术—航空宇航推进理论与工程]