Study of Cavitation Thermodynamic Effect of Liquid Rocket Engine Inducer

被引：0

作者：

Xiang L. ^{[1
,3
]}

Chen H. ^{[1
,3
]}

Tan Y.-H. ^{[1
,2
,3
]}

Liu S.-X. ^{[3
]}

Xu K.-F. ^{[3
]}

Zhang Y.-T. ^{[1
,3
]}

机构：

[1] Science and Technology on Liquid Rocket Engine Laboratory, Xi'an Aerospace Propulsion Institute, Xi'an

[2] Academy of Aerospace Propulsion Technology, Xi'an

[3] Xi'an Aerospace Propulsion Institute, Xi'an

来源：

Xiang, Le (13126986485@163.com) | 1600年 / Journal of Propulsion Technology卷 / 41期

关键词：

Cavitation; Inducer; Liquid rocket engine; Thermodynamic effect; Visualization;

D O I：

10.13675/j.cnki.tjjs.190139

中图分类号：

学科分类号：

摘要：

To study the cavitation thermodynamic effect, a series of visualization experiments of the cavitating flow inside a model inducer were carried out under different flow coefficients and temperatures, the cavitation structures were documented integrally from the inception point to the breakdown point. It is found that temperature shows little influence on the non-cavitation hydraulic performance, but the breakdown point is remarkably delayed at high temperatures, indicating the influence of the thermodynamic effect. The comparison of cavitation structures at different temperatures implies that the strength of thermodynamic effect is closely related to the flow condition and it is more conspicuous at smaller cavitation numbers. At last, a semi-empirical theoretical model was introduced to predict the influence of thermodynamic effect on the cavitation performance. The averaged deviation between predicted and experimental results is 5.5% at small flow condition (Φ=0.071). The averaged deviation is 10.8% for the larger flow condition (Φ=0.088). Thus the validity of the predicted model is verified in the investigated conditions in this study. © 2020, Editorial Department of Journal of Propulsion Technology. All right reserved.

引用

页码：812 / 819

页数：7

共 18 条

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