Investigation on working course of supersonic self-ejector

ZHANG Min-qin; ZHANG Zhong-li; ZHOU Li-xin; ZHANG Meng-zheng

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Investigation on working course of supersonic self-ejector

更新时间：2026-07-07

- Investigation on working course of supersonic self-ejector
- Vol. 27, Issue 1, (2012)
- 作者机构：
  
  1. 西北工业大学航天学院,西安,71007
  2. 中国航天科技集团公司西安航天动力研究所,西安,710100
- 作者简介：
- 基金信息：
- DOI：
  CLC：
- Published：2012
- 稿件说明：
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ZHANG Min-qin, ZHANG Zhong-li, ZHOU Li-xin, et al. Investigation on working course of supersonic self-ejector[J]. 2012, 27(1).
DOI：

ZHANG Min-qin, ZHANG Zhong-li, ZHOU Li-xin, et al. Investigation on working course of supersonic self-ejector[J]. 2012, 27(1). DOI：

摘要

应用湍流κ-ε双方程模型

分析了液体火箭发动机自引射工作过程所用的超声速自引射装置(简称引射器

包括圆柱型和二次喉道型引射器)在相同二次流入口面积时的流场分布

依据流场分析值确定了激波在引射器内的位置

结果表明喷管内的气流达到满流状态

并根据有关参数计算了引射系数.对比引射器真空舱内压力仿真值和试车测量值

两者基本一致.

Abstract

The analysis model of self-ejector(ejector for short

including cylindrical ejector and second-throat ejector) was set up in liquid rocket engine.The two equation κ-ε model was employed to simulate the turbulence.The performances and the flow field features of cylindrical and second-throat ejector were gained in same gap.According as these flow fields

the site of the shock wave

the full flow in nozzle

the coefficients of ejecting were calculated.The numerical value was compared with hot fire test value in vacuum cabin

both are same.

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