氢氧发动机真空羽流干扰试验研究

吴靖; 蔡国飙; 贺碧蛟

doi:10.13700/j.bh.1001-5965.2018.0233

氢氧发动机真空羽流干扰试验研究

doi: 10.13700/j.bh.1001-5965.2018.0233

1.
福州大学机械工程及自动化学院, 福州 350116
2.
北京航空航天大学宇航学院, 北京 100083

详细信息

作者简介:
吴靖男, 博士, 讲师, 硕士生导师。主要研究方向:真空羽流及其效应、流场显示

蔡国飙男, 博士, 教授, 博士生导师。主要研究方向:真空羽流及其效应、火箭发动机仿真优化设计与重复使用技术、固液混合火箭发动机技术及应用

贺碧蛟男, 博士, 教授, 硕士生导师。主要研究方向:真空羽流及其效应

通讯作者:
吴靖, E-mail: wujing@fzu.edu.cn

中图分类号: V411.7
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- 被引次数: 0
出版历程
- 收稿日期: 2018-04-26
- 录用日期: 2018-05-25
- 网络出版日期: 2019-01-20

Experimental investigation on vacuum plume interaction of hydrogen/oxygen engines

WU Jing^{1
, ,},
CAI Guobiao²,
HE Bijiao²

1.
College of Mechanical Engineering and Automation, Fuzhou University, Fuzhou 350116, China
2.
School of Astronautics, Beihang University, Beijing 100083, China

More Information

Corresponding author: WU Jing, E-mail: wujing@fzu.edu.cn

摘要

摘要:
为了研究航天器发动机多股羽流产生的羽流干扰对流场结构及参数的影响，在北京航空航天大学真空羽流效应试验系统（PES）中，采用总压皮托管阵列对60 N氢氧模拟发动机单机羽流和双机干扰羽流的压力场进行了测量。试验结果表明：单机羽流流场压力随着轴向距离的增大而迅速降低；受到钟形喷管产生的压缩波束影响，同一轴向距离上的压力最大值逐渐偏离喷管轴线；双机羽流干扰发生于两股发动机羽流主流之间的区域，干扰流的作用范围和强度随着轴向距离的增大而增大，干扰流压力最高可以达到单机羽流相同位置处压力的5倍以上；受到干扰流压缩波束边界的影响，同一轴向距离上的压力最大值逐渐偏离双发动机对称面。
- 真空羽流 /
- 羽流干扰 /
- 氢氧发动机 /
- 压力场 /
- 压缩波束
Abstract:
To investigate the effects of plume interaction caused by multiple spacecraft engines on the flow field structure and parameters, the pressure fields of single plume and dual plumes generated by hydrogen/oxygen engines with 60 N thrust were determined using a pitot tube array in vacuum plume effect experimental system (PES) of Beihang University. The experimental results show that the pressure in the single plume field decreases rapidly with the increase of axial distance, and the location of the maximum pressure along the same axial distance gradually deviates from the nozzle axis due to the compression waves generated from the bell nozzle. Plume interaction occurs in the region between the dual prime plumes, whose action range and intensity increase with the increase of axial distance. To the highest degree, the pressure of the interacted plume can be more than 5 times that of the single plume at the same point. The location of the maximum pressure along the same axial distance gradually deviates from the symmetry plane of the dual engines due to the compression waves' boundary of the interacted plume.
- vacuum plume /
- plume interaction /
- hydrogen/oxygen engine /
- pressure field /
- compression waves

HTML全文

图 1 PES真空舱

Figure 1. Vacuum chamber of PES

下载: 全尺寸图片幻灯片

图 2 氢氧模拟发动机结构

Figure 2. Structure of simulated hydrogen/oxygen engine

下载: 全尺寸图片幻灯片

图 3 皮托管阵列及微差压传感器示意图

Figure 3. Schematic of pitot tube array and differential pressure transducer

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图 4 试验系统空间位置关系

Figure 4. Spatial relation of experimental system

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图 5 大气环境下氢氧发动机单机和双机热试车

Figure 5. Hot firing tests of single and dual hydrogen/oxygen engine(s) in atmospheric environment

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图 6 氢氧发动机单机羽流流场波后压力云图

Figure 6. Plume flow field contour of pressure behind shock wave for single hydrogen/oxygen engine

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图 7 氢氧发动机双机干扰羽流流场波后压力云图

Figure 7. Interacted plume flow field contour of pressure behind shock wave for dual hydrogen/oxygen engines

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图 8 不同轴向距离的单机和双机羽流流场波后总压对比

Figure 8. Comparison of plume flow field's total pressure behind shock wave between single engine and dual engines at different axial distances

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表 1 不同轴向距离x对应的双机对称面所在的y坐标

Table 1. y coordinate at symmetry plane of dual engines corresponding to different axial distances x

mm
轴向距离x	对称面y坐标
140	81.2
166	82.3
240	85.6
350	90.4
450	94.7
600	99.3

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参考文献(17)

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