二次燃烧对多喷管运载火箭底部热环境影响研究

周志坛; 李怡庆; 江平; 包轶颖

doi:10.13224/j.cnki.jasp.20210694

二次燃烧对多喷管运载火箭底部热环境影响研究

doi: 10.13224/j.cnki.jasp.20210694

1.
南昌航空大学飞行器工程学院，南昌 330063
2.
上海宇航系统工程研究所，上海 201109

基金项目: 江西省自然科学青年基金（20224BAB211010）

详细信息

作者简介:
周志坛（1993-），男，讲师、硕士生导师，博士，主要从事高超声速飞行器力/热环境研究

中图分类号: V19
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- 文章访问数: 38
- HTML浏览量: 20
- PDF量: 6
- 被引次数: 0
出版历程
- 收稿日期: 2021-12-06
- 网络出版日期: 2024-01-23

Effect of secondary combustion on the multi-nozzle rocket base thermal environment

1.
School of Aircraft Engineering，Nanchang Hangkong University，Nanchang 330063，China
2.
Shanghai Institute of Aerospace System Engineering，Shanghai 201109，China

摘要

摘要:
火箭飞行时，尾焰中富燃燃气将继续与空气中氧气发生二次燃烧，导致尾流场温度升高。基于三维可压缩Navier-Stokes方程、混合RANS/LES湍流模型、DOM辐射模型和有限速率化学动力学模型建立多喷管火箭尾焰反应流模型，并通过与风洞试验数据对比验证了模型有效性。基于此，开展了6个不同高度下双喷管火箭和四喷管火箭反应流与冻结流流场对比分析。研究表明：二次燃烧主要发生在羽流混合层中，引起的流场峰值温度增幅随飞行高度增加而减小，最高可达10.16%，最低仅为0.86%。同一高度下，当羽流由近场向远场转变时，二次燃烧效应逐渐增强。相较于双喷管火箭，二次燃烧对四喷管火箭底部热环境影响更小。另外，多喷管火箭底部峰值热流随高度增加基本表现为先增大后减小的趋势。
- 二次燃烧 /
- 多喷管运载火箭 /
- 热环境 /
- 反应流 /
- 冻结流
Abstract:
During rocket launching, the secondary combustions between the fuel-rich exhaust gas and the oxygen of air were made, leading to a temperature rise. Based on three-dimensional compressible Navier-Stokes equation, hybrid RANS/LES turbulence model, DOM model, and finite-rate chemical kinetics, the reaction model of multi-nozzle rocket was established. And the validity of model was verified by comparing with the wind tunnel experimental data. Then, a comparison study between reaction and frozen flows of two-/four-nozzle rockets was developed. The results showed that the secondary combustion mainly occurred in the mixed layer. With the increase of the flight altitudes, the increase of the peak temperature caused by afterburning decreased, while the maximum was 10.16% and the minimum was 0.86%. At the same height, the afterburning effect was strengthened with increasing distance from nozzle exit. Comparing with two-nozzle rocket, the afterburning had less effect on the four-nozzle rocket base thermal environment. In addition, the peak heat flux of the rocket base increased first and then decreased with height.
- secondary combustion /
- multi-nozzle rocket /
- thermal environment /
- reaction flow /
- frozen flow

HTML

图 1 多喷管运载火箭几何模型

Figure 1. Geometric models of the multi-nozzle rockets

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图 2 多喷管运载火箭结构网格

Figure 2. Structured grids of the multi-nozzle rockets

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图 3 网格无关性分析

Figure 3. Grid independence verification

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图 4 算例几何与网格模型

Figure 4. Test model and its computational model

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图 5 数值结果与试验结果对比

Figure 5. Comparison between numerical results and experimental data

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图 6 多喷管运载火箭尾焰马赫数云图

Figure 6. Mach number contours of multi-nozzle rockets exhaust plume

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图 7 四喷管运载火箭羽流诱导激波

Figure 7. Plume induced shock of four-nozzle rockets

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图 8 多喷管运载火箭尾焰温度云图

Figure 8. Temperature contours of multi-nozzle rockets exhaust plume

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图 9 火箭尾焰温度峰值

Figure 9. Maximum temperature of the rocket exhaust plumes

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图 10 双喷管运载火箭羽流温度截面图

Figure 10. Planar temperature contours of two-nozzle rocket exhaust plume

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图 11 四喷管运载火箭羽流温度截面图

Figure 11. Planar temperature contours of four-nozzle rocket exhaust plume

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图 12 多喷管运载火箭底部热流云图

Figure 12. Base heat flux of multi-nozzle rockets

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图 13 多喷管运载火箭反应流温度等值面

Figure 13. Temperature iso-surface of multi-nozzle rocket exhaust flowfields

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图 14 多喷管火箭底部热流峰值

Figure 14. Peak heat flux of the multi-nozzle rocket base

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表 1 H₂/CO/O₂二次燃烧反应体系

Table 1. Reaction mechanism of H₂/CO/O₂ afterburning

反应方程式	A_r/（m, kmol, s）	N_T	E_Ar/（J/kmol）
H₂+O=OH+H	5.17×10⁸	2.27	2.91×10⁷
H+O₂=OH+O	3.18×10¹¹	−0.49	6.75×10⁷
OH+H₂=H₂O+H	5.89×10⁸	1.88	1.32×10⁷
OH+OH=H₂O+O	3.40×10⁷	2.26	−7.47×10⁶
O+H+M=OH+M	1.58×10¹⁰	−1.00	0
H+H+M=H₂+M	4.96×10⁹	−1.21	2.56×10⁶
H+OH+M=H₂O+M	7.83×10¹¹	−2.54	5.05×10⁵
O+O+M=O₂+M	1.89×10⁷	0.00	−7.48×10⁶
CO+OH=CO₂+H	5.19×10⁶	2.22	−5.78×10⁷
CO+O+M=CO₂+M	6.17×10⁸	0	1.26×10⁷

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表 2 喷管入口气体摩尔组分

Table 2. Gas mole fractions at the nozzle inlet

组分	摩尔分数
H₂O	0.39
CO₂	0.26
CO	0.25
H₂	0.06
H	0.03
OH	0.01

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表 3 不同高度下的来流条件

Table 3. Freestream conditions under different altitudes

飞行高度/km	压强/Pa	温度/K	来流马赫数
15	11960	217	1.54
20	6587	217	1.96
25	2616	221	2.40
30	1210	226	2.84
35	580	236	3.24
40	300	249	3.60

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