火箭推进

为了研究超声速进气道在旋转反压作用下的流动特性,建立了旋转爆震发动机周期性反压简化模型,以双下侧进气道为研究对象,采用非定常数值仿真手段开展了旋转爆震反压作用下进气道内流动特性仿真。结果表明:在进气道出口畸变流动条件下,周期性旋转反压作用下的进气道内压力波面呈现不规则螺旋状,与均匀来流隔离段内规则螺旋状流动存在一定差异; 旋转反压在两侧进气道交汇处受到阻断,两侧进气道在交汇截面之前趋于稳定流动,周期性反压和稳态反压对应的进气道激波串前缘位置基本一致,说明进气道周期性反压作用下性能与稳态情况下一致。

In order to study the flow characteristics of the rotating detonation engine inlet under the action of rotating back pressure,a simplified model of the periodic backpressure of the rotating detonation engine was established, and the unsteady numerical simulation method was used to study the flow characteristics of the twin inlet under the action of rotating detonation back pressure.The results show that the iso-pressure surface of the flowfield presents an irregular spiral shape under the action of periodic rotating back pressure with the distorted flow condition,which is different from the flow characteristic in the isolation section of uniform inlet flow.The rotating pressure wave is blocked at the intersection of the two ducts, and the flow of two ducts tends to be steady before the intersection section.The leading edge of the shock train at the end of the inlet is basically the same under periodic rotating back pressure and steady state back pressure, indicating that the performance under the periodic backpressure of the inlet is not different from that under the steady-state condition.

引言
1 数值仿真模型
2 旋转反压模型
3 旋转爆震反压周期性扰动下进气道流动特性
4 结论

图1 进气道布局形式<br/>Fig.1 Inlet configuration

图1 进气道布局形式
Fig.1 Inlet configuration

图2 进气道计算网格
Fig.2 Inlet grid domain

图3 旋转爆震发动机燃烧室压力曲线<br/>Fig.3 Pressure curve of combustion chamber of a rotating detonation engine

图3 旋转爆震发动机燃烧室压力曲线
Fig.3 Pressure curve of combustion chamber of a rotating detonation engine

图4 旋转爆震压力曲线建模<br/>Fig.4 Modeling of rotating detonation pressure curve

图4 旋转爆震压力曲线建模
Fig.4 Modeling of rotating detonation pressure curve

图5 周期性燃烧室反压<br/>Fig.5 Periodic rotation detonation pressure curve

图5 周期性燃烧室反压
Fig.5 Periodic rotation detonation pressure curve

图6 进气道内压力监测点<br/>Fig.6 Pressure monitoring points in the inlet

图6 进气道内压力监测点
Fig.6 Pressure monitoring points in the inlet

表1 进气道压力监测点位置坐标<br/>Tab.1 Position of inlet pressure monitoring point

表1 进气道压力监测点位置坐标
Tab.1 Position of inlet pressure monitoring point

图7 周期性反压扰动下流场压力图<br/>Fig.7 Flow field pressure contour under periodic back pressure disturbance

图7 周期性反压扰动下流场压力图
Fig.7 Flow field pressure contour under periodic back pressure disturbance

图8 周期性反压扰动下壁面压力云图<br/>Fig.8 Wall pressure contour under periodic back pressure disturbance

图8 周期性反压扰动下壁面压力云图
Fig.8 Wall pressure contour under periodic back pressure disturbance

图9 进气道内监测点压力变化<br/>Fig.9 Pressure curve of monitoring point in inlet

图9 进气道内监测点压力变化
Fig.9 Pressure curve of monitoring point in inlet

图10 周期性反压及稳态反压对进气道激波串位置影响<br/>Fig.10 Influence of periodic and steady backpressure onposition of inlet shock train

图10 周期性反压及稳态反压对进气道激波串位置影响
Fig.10 Influence of periodic and steady backpressure onposition of inlet shock train

图11 进气道内监测点压力变化<br/>Fig.11 Pressure curve of monitoring point in inlet

图11 进气道内监测点压力变化
Fig.11 Pressure curve of monitoring point in inlet

图12 周期性反压扰动下流场压力图<br/>Fig.12 Flow field pressure contour under periodic back pressure disturbance

图12 周期性反压扰动下流场压力图
Fig.12 Flow field pressure contour under periodic back pressure disturbance

图13 进气道流道内压力不同时刻变化曲线<br/>Fig.13 The curve of the pressure in the inlet at different moments

图13 进气道流道内压力不同时刻变化曲线
Fig.13 The curve of the pressure in the inlet at different moments

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备注

引言

1 数值仿真模型

2 旋转反压模型

3 旋转爆震反压周期性扰动下进气道流动特性

4 结论

期刊信息