航天推进技术研究院主办
[1]张 明,孙 冰.液氧/甲烷发动机变截面冷却通道传热数值研究[J].火箭推进,2019,45(02):9-15.
ZHANG Ming,SUN Bing.Numerical study of heat transfer in variable cross-section cooling channels of LOX/methane rocket engines[J].Journal of Rocket Propulsion,2019,45(02):9-15.
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ZHANG Ming,SUN Bing.Numerical study of heat transfer in variable cross-section cooling channels of LOX/methane rocket engines[J].Journal of Rocket Propulsion,2019,45(02):9-15.
液氧/甲烷发动机变截面冷却通道传热数值研究
《火箭推进》[ISSN:1672-9374/CN:CN 61-1436/V]
卷:
45
期数:
2019年02期
页码:
9-15
栏目:
研究与设计
出版日期:
2019-04-30
- Title:
- Numerical study of heat transfer in variable cross-section cooling channels of LOX/methane rocket engines
- 文章编号:
- 1672-9374(2019)02-0009-07
- Keywords:
- methane; transcritical; coupled heat transfer; rocket engine; regenerative cooling; sudden contraction/sudden expansion
- 分类号:
- V434.14
- 文献标志码:
- A
- 摘要:
- 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。
- Abstract:
- 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.
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相似文献/References:
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[2]李军伟,钟北京,熊耀宇,等.甲烷/氧气双组元微型推力室的实验研究[J].火箭推进,2007,33(06):1.
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备注/Memo
收稿日期:2018-06-30; 修回日期:2018-08-05 作者简介:张 明(1993—),男,硕士,研究领域为液体火箭发动机热防护
更新日期/Last Update:
2019-04-30