火箭推进

燃料喷孔数对非预混旋转爆震起爆过程的影响

(1.西北工业大学动力与能源学院,陕西西安 710129; 2.西安航天动力研究所液体火箭发动机技术重点实验室,陕西西安 710100)

Effects of the number of fuel injection orifices on rotating detonation initiation process under non-premixed conditions

JIAO Zhongtian^1,2,WANG Yongjia²,LI Wei¹,ZHU Yiyuan¹,WANG Ke¹,FAN Wei¹

(1. School of Power and Energy,Northwestern Polytechnical University,Xi'an 710129, China; 2.Science and Technology on Liquid Rocket Engine Laboratory,Xi'an Aerospace Propulsion Institute,Xi'an 710100, China)

Keywords：rotating detonation; non-premixed injection; injection orifice number; numerical simulation; propagation mode

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环缝-喷孔结构是目前旋转爆震燃烧中经常采用的喷注结构之一。为了研究环缝-喷孔喷注结构中燃料喷孔数量对氢气/空气旋转爆震的影响,在保持燃料喷孔总面积不变的前提下,改变燃料喷孔数量(60、90、120、150),对冷态混合、爆震波起爆及稳定过程进行了数值模拟。总质量流量为206 g/s时,60和90喷孔喷注结构可以实现稳定爆震,而120和150喷孔则起爆失败; 60喷孔构型中出现了多个旋转爆震波,并稳定于双波同向传播模态。总质量流量减小至103 g/s时,120和150喷孔可实现稳定爆震。结果表明,同一喷注结构在不同流量下的掺混效果并不相同,影响旋转爆震的起始; 随着供给流量的提高,爆震波数量呈现增多趋势; 氢气的轴向和径向分布越均匀,越容易形成旋转爆震波,周向分布越均匀,旋转爆震波传播速度越快,最高可达1 827 m/s。

Slot-orifice injection scheme is now commonly used in rotating detonations. The influence of the number of fuel injection orifices(60,90,120,150)on rotating detonations inside an annular combustor were investigated numerically including the mixing process,the detonation initiation process and the detonation propagation process. For a total mass flow rate of 206 g/s,stable rotating detonation waves can be obtained when 60 and 90 orifices were used,while rotating detonation fails to be produced when 120 and 150 orifices were used. Multi-waves appeared in the 60 orifices configuration which finally transits into a stable dual-wave mode. When the total mass flow rate decreased to 103 g/s,stable detonation wave was able to be formed in the 120 and 150 orifices configurations. The results indicate that the mixing process of the same injection configuration will be affected by the mass flow rate,which has a great impact on the detonation initiation. If distribution of H2 in axialand radial directions is more uniform,the detonation initiation becomes easier. It is also observed that the detonation wave number increases with the mass flow rate. Moreover,a more uniform distribution of H2 in the circumferential direction will lead to a faster detonation velocity,and a highest velocity of 1 827 m/s has been obtained.

引言
1 数值方法及计算模型
2 冷态流场
3 起爆及传播过程分析
4 结论

表1 单步氢气/空气反应机理<br/>Tab.1 Parameters of the single step hydrogen/air reaction mechanism

表1 单步氢气/空气反应机理
Tab.1 Parameters of the single step hydrogen/air reaction mechanism

图1 非预混喷注旋转爆震燃烧室模型<br/>Fig.1 Model of a RDC employing non-premixed injection

图1 非预混喷注旋转爆震燃烧室模型
Fig.1 Model of a RDC employing non-premixed injection

表2 物理计算模型尺寸参数<br/>Tab.2 Dimensions of the physical model for simulations

表2 物理计算模型尺寸参数
Tab.2 Dimensions of the physical model for simulations

表3 物理计算模型的可变尺寸<br/>Tab.3 Variable dimensions of the physical mode for simulation

表3 物理计算模型的可变尺寸
Tab.3 Variable dimensions of the physical mode for simulation

图2 当量比与相对当量比的关系<br/>Fig.2 Functional relation between φ and Er

图2 当量比与相对当量比的关系
Fig.2 Functional relation between φ and Er

表4 各喷注结构的喷注间隔与穿透系数<br/>Tab.4 Injection orifices interval and penetrating coefficient of different injection configurations

表4 各喷注结构的喷注间隔与穿透系数
Tab.4 Injection orifices interval and penetrating coefficient of different injection configurations

图3 供给流量为206 g/s时不同喷孔数的燃烧室中径相对当量比变化云图<br/>Fig.3 Contours of Er in the combustion chamber under a flow rate of 206 g/s with different injection orifice numbers

图3 供给流量为206 g/s时不同喷孔数的燃烧室中径相对当量比变化云图
Fig.3 Contours of Er in the combustion chamber under a flow rate of 206 g/s with different injection orifice numbers

图4 供给流量为206 g/s时不同喷孔数下x=0 mm截面相对当量比变化云图<br/>Fig.4 Contours of Er in the combustion chamber under a flow rate of 206 g/s with different injection orifice numbers(x=0 mm)

图4 供给流量为206 g/s时不同喷孔数下x=0 mm截面相对当量比变化云图
Fig.4 Contours of Er in the combustion chamber under a flow rate of 206 g/s with different injection orifice numbers(x=0 mm)

图5 不同供给流量下R=33 mm截面相对当量比的变化<br/>Fig.5 Contours of Er under different flow rates for the injection configuration with 60 orifices(R=33 mm)

图5 不同供给流量下R=33 mm截面相对当量比的变化
Fig.5 Contours of Er under different flow rates for the injection configuration with 60 orifices(R=33 mm)

图6 不同供给流量下相对当量比分布及气流轴向速度的流线分布<br/>Fig.6 Contours of Er and axial velocity under different flow rates in the configuration with 60 orifices

图6 不同供给流量下相对当量比分布及气流轴向速度的流线分布
Fig.6 Contours of Er and axial velocity under different flow rates in the configuration with 60 orifices

图7 不同供给流量下相对当量比随轴向、周向和径向位置的变化<br/>Fig.7 Variation of Er rh the flow rate in axial,circumferential and radial directions

图7 不同供给流量下相对当量比随轴向、周向和径向位置的变化
Fig.7 Variation of Er rh the flow rate in axial,circumferential and radial directions

图8 喷孔数为90时爆震波发展过程<br/>Fig.8 The initiation and propagation process in the case with 90 injection orifices

图8 喷孔数为90时爆震波发展过程
Fig.8 The initiation and propagation process in the case with 90 injection orifices

图9 喷孔个数为150时爆震波发展过程<br/>Fig.9 The initiation and propagation process in the case with 150 injection orifices

图9 喷孔个数为150时爆震波发展过程
Fig.9 The initiation and propagation process in the case with 150 injection orifices

图10 喷孔数为60时爆震波发展过程<br/>Fig.10 The initiation and propagation process in the case with 60 injection orifices

图10 喷孔数为60时爆震波发展过程
Fig.10 The initiation and propagation process in the case with 60 injection orifices

图11 不同喷孔数量下稳定爆震流场的压力云图<br/>Fig.11 Pressure contours of the RDC obtained with different injection orifice numbers

图11 不同喷孔数量下稳定爆震流场的压力云图
Fig.11 Pressure contours of the RDC obtained with different injection orifice numbers

图12 不同喷孔数量下得到的旋转爆震波压力曲线<br/>Fig.12 Pressure history obtained in the cases with different injection orifice numbers

图12 不同喷孔数量下得到的旋转爆震波压力曲线
Fig.12 Pressure history obtained in the cases with different injection orifice numbers

表5 各工况计算结果<br/>Tab.5 Numerical results under different operating conditions

表5 各工况计算结果
Tab.5 Numerical results under different operating conditions

$图13 喷孔个数为90时的温度和氢气质量分数分布<br/>Fig.13 Contours of temperature and mass fraction of hydrogen in the chamber with 90 injection orifices$

图13 喷孔个数为90时的温度和氢气质量分数分布
Fig.13 Contours of temperature and mass fraction of hydrogen in the chamber with 90 injection orifices

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火箭推进
JOURNAL OF ROCKET PROPULSION

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标准刊号 ISSN 1672-9374
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引言

1 数值方法及计算模型

2 冷态流场

3 起爆及传播过程分析

4 结论

期刊信息