Simulation of flow characteristics and performance of vortex cooling thrust chamber

被引：0

作者：

Li, Gong-Nan ^{[1
]}

Yu, Nan-Jia ^{[1
]}

Lu, Qiang ^{[1
]}

机构：

[1] School of Astronautics, Beijing University of Aeronautics and Astronautics

来源：

Hangkong Dongli Xuebao/Journal of Aerospace Power | 2014年 / 29卷 / 02期

关键词：

Dual vortex structure; Flow characteristics; Numerical simulation; Thrust chamber performance; Vortex cooling;

D O I：

10.13224/j.cnki.jasp.2014.02.022

中图分类号：

学科分类号：

摘要：

Numerical simulation of 3-D full-size model was conducted for 2 000 N gas hydrogen/gas oxygen vortex cooling thrust chamber. Velocity distribution characteristics of the flow field were obtained, and existence of the bidirectional vortex structure was verified. The interface of inner and outer vortexes accounted for 86% of the thrust chamber cylinder radius, and the combustion zone took up 70% of the thrust chamber cylinder radius. Analysis showed that the outer vortex cooling layer was mainly influenced by incoming stream velocity and geometric parameters of thrust chamber. The pressure and density of the inner vortex maintained stable due to the viscosity and combustion. The average temperature of the thrust chamber sidewall was 388 K. The specific efficiency was above 92%. The results of computation were consistent with the experiment results.

引用

页码：420 / 426

页数：6

共 15 条

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