液体火箭发动机泵的POGO气蚀动特性试验研究  

Experimental investigation of POGO cavitation dynamic characteristic for liquid rocket engine pump

作　　者：王珺[1] 胡鹏[1] 颜勇[1] 

机构地区：[1]北京航天动力研究所,北京100076

出　　处：《火箭推进》2012年第4期26-31,共6页Journal of Rocket Propulsion

基　　金：国家"863"项目(2007AA705302)

摘　　要：为获取液体火箭发动机泵的POGO动特性参数,围绕泵的气蚀动特性开展了一系列试验研究。首先描述了试验系统,阐述了试验原理;其次,以泵入口0.5 MPa工况为例,介绍了试验数据的分析过程;最后,结合试验数据给出了气蚀柔度、动态增益等动特性参数的试验结果。结果表明,在泵入口压力0.25～0.86 MPa范围内,无量纲气蚀柔度约为0.6～2,动态增益主要集中在2～5,最高达到13。A series of experimental investigations were performed in order to obtain the POGO dynamic parameters of liquid rocket engine pump. The experimental system is described and the main test principle is expounded. The analysis progress of test data at pump inlet pressure of 0.5 MPa is in troduced. Based on test results, the POGO dynamic characteristic parameters, such as cavitation compliance and pump dynamic gain, are given. The investigation shows that, under the condition of pump inlet pressure of 0.25-0.86 MPa, the non-dimensional cavitation compliance is 0.6-2, the pump dynamic gain is 2-5 and the maximum observation value is up to 13.

关 键 词：泵气蚀动特性参数 POGO 试验系统 气蚀柔度 动态增益 

分 类 号：V434-34[航空宇航科学与技术—航空宇航推进理论与工程]