火箭推进

为提高液体火箭发动机推力室再生冷却通道的冷却效率,对液氧/甲烷发动机推力室变截面冷却通道的耦合传热进行数值模拟,探究了冷却通道的高宽比对跨临界甲烷的湍流流动和对流传热的影响。燃气-冷却通道-冷却剂的三维耦合计算采用一种改进的迭代耦合方法。研究结果表明:在冷却通道横截面积不变时,增大冷却通道高宽比可以降低喉部燃气侧壁面最高温度。冷却通道的高宽比越大,冷却剂压力损失越大。但过大的高宽比会导致压力损失急剧增大,且进一步降低喉部壁面最高温度的效果不明显。燃气侧壁面温度在变截面冷却通道的突扩突缩处出现局部下降,且下降幅度会随着高宽比的减小而增加。大高宽比冷却通道中,喉部侧壁面附近发生传热恶化的范围有限,主要在肋侧壁面附近的下半部分。研究结果为推力室变截面再生冷却通道的设计提供了参考。

In order to improve the cooling efficiency of regenerative cooling channels of liquid rocket engine thrust chamber, the numerical simulation of the coupled heat transfer in the variable cross-section cooling channels of the LOX/methane engine thrust chamber was carried out to investigate the effects of the aspect ratio on the turbulent flow and convective heat transfer of the transcritical methane in this paper.An improved iterative coupling method was used for the three-dimensional coupling calculation of the hot gas, the cooling channel and the coolant domain.The research results show that when the cooling channel cross-sectional area is constant, increasing the aspect ratio of the cooling channel can reduce the maximum hot-gas-side wall temperature at the throat.The larger the cooling channel aspect ratio is, the greater the coolant pressure loss is.However, excessive aspect ratio will lead to a sharp increase in pressure loss, and the effect of further reducing the maximum temperature of the hot-gas-side wall at the throat is not obvious.The hot-gas-side wall temperature drops at the sudden contraction/sudden expansion structures of variable cross-section cooling channel.And the magnitude of the decrease increases as the aspect ratio decreases.In the large aspect ratio cooling channel, the area where the heat transfer deterioration occurs near the lateral wall surface at the throat is limited, mainly in the lower half of the rib side wall.This paper provides a reference for the design of variable cross-section regenerative cooling channels of the thrust chamber.

引言
1 数值计算方法
2 计算结果与分析
3 结论

表1 变截面冷却通道的参数<br/>Tab.1 The parameters of variable section cooling channels

表1 变截面冷却通道的参数
Tab.1 The parameters of variable section cooling channels

图1 3种网格级别下燃气侧壁面温度沿程变化<br/>Fig.1 Variations of hot-gas-side wall temperature along the axial direction for three grid levels

图1 3种网格级别下燃气侧壁面温度沿程变化
Fig.1 Variations of hot-gas-side wall temperature along the axial direction for three grid levels

图2 数值网格划分
Fig.2 Numerical gird

图3 燃气侧壁面温度和热流密度沿轴向的变化<br/>Fig.3 Variation of hot-gas-side wall temperature and heat flux along the axial direction

图3 燃气侧壁面温度和热流密度沿轴向的变化
Fig.3 Variation of hot-gas-side wall temperature and heat flux along the axial direction

图4 冷却剂静压沿程变化<br/>Fig.4 Variation of coolant static pressure along the axial direction

图4 冷却剂静压沿程变化
Fig.4 Variation of coolant static pressure along the axial direction

图5 冷却剂流速沿程变化<br/>Fig.5 Variation of coolant velocity along the axial direction

图5 冷却剂流速沿程变化
Fig.5 Variation of coolant velocity along the axial direction

图6 冷却剂螺旋度沿轴向的变化<br/>Fig.6 Variation of coolant helicity along the axial direction

图6 冷却剂螺旋度沿轴向的变化
Fig.6 Variation of coolant helicity along the axial direction

图7 喉部截面冷却剂的流线<br/>Fig.7 Streamlines of coolant at the throat

图7 喉部截面冷却剂的流线
Fig.7 Streamlines of coolant at the throat

图8 喉部燃气侧壁面最高温度和冷却剂压降的变化<br/>Fig.8 Variation of the maximum hot-gas-side wall temperature at the throat and pressure drop of the coolant

图8 喉部燃气侧壁面最高温度和冷却剂压降的变化
Fig.8 Variation of the maximum hot-gas-side wall temperature at the throat and pressure drop of the coolant

图9 喉部截面冷却剂的温度分布<br/>Fig.9 The coolant temperature distribution at the throat

图9 喉部截面冷却剂的温度分布
Fig.9 The coolant temperature distribution at the throat

图10 喉部截面壁面的温度分布<br/>Fig.10 The wall temperature distribution at the throat

图10 喉部截面壁面的温度分布
Fig.10 The wall temperature distribution at the throat

图11 喉部截面冷却剂的比定压热容分布<br/>Fig.11 Specific heat capacity distribution of the coolant at the throat

图11 喉部截面冷却剂的比定压热容分布
Fig.11 Specific heat capacity distribution of the coolant at the throat

图12 喉部截面冷却剂的导热系数分布<br/>Fig.12 Thermal conductivity distribution of the coolant at the throat

图12 喉部截面冷却剂的导热系数分布
Fig.12 Thermal conductivity distribution of the coolant at the throat

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备注

引言

1 数值计算方法

2 计算结果与分析

3 结论

期刊信息