Numerical study of vortex breaker optimization in a first stage oxygen tank

IF 5.4 2区 工程技术 Q1 ENGINEERING, AEROSPACE
Yixiu Shen , Yimeng Li , Zhenggang Du
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Abstract

One of the crucial factors affecting the carrying capacity of the cryogenic liquid launch vehicle is the effective volume of the tank. Theoretical and experimental investigations on vortex breaker mechanisms have proposed promising schemes applied in the oxygen tank of the liquid-propellant launch vehicle to ensure the normal operation of the engine. In this paper, the liquid surface profile functions of the laminar core when the vortex generates were derived based on the Rankine vortex model. The dimensionless residual volume V/d3 and the Froude number were applied to compare the theoretical prediction of critical height with the actual simulation data of liquid oxygen. This comparison method can improve the model's accuracy. The efficiency of different basic shapes of vortex breakers was tested by conducting CFD modelling on a non-vertical outflow tank under a specific operating condition. Simulation results suggest negligible effects of heat transfer and surface tension. A circular plate is considered the optimal vortex breaker shape in traditional vertical outflow tanks, while a higher optimize efficiency was discovered in the half baffle basic shape in a non-vertical outflow tank by comparing the dimensionless residual volume and flow coefficient. A 34.26% reduction in flow resistance of half baffle breaker can be reached when applying a twenty-degree outlet pipe chamfering setting compared to a zero-degree chamfer. Considering practical operating limitations, it is concluded that a vortex breaker mechanism in a half baffle basic shape with a radius of 2.5d and a height of 4/d is the optimal scheme, which is suitable for all types of tanks. Its optimization efficiency of the residual volume reduction is about 56.68% compared to a no-breaker installation case. Lastly, a general equation based on CFD simulation for predicting the residual volume under a certain outflow velocity was proposed: V/d3αFr0.3, which trend is consistent with that of mathematical prediction V/d3αFr1/3. This consistency proves the accuracy and applicability of optimization strategy in this paper.

一级氧气罐破涡器优化的数值研究
影响低温液体运载火箭运载能力的关键因素之一是储罐的有效容积。通过对破涡机构的理论和实验研究,提出了应用于液体推进剂运载火箭氧气罐以确保发动机正常运行的有前景的方案。本文基于Rankine涡模型,推导了产生涡流时层流核心的液面轮廓函数。应用无量纲残余体积V/d3和弗劳德数将临界高度的理论预测与液氧的实际模拟数据进行了比较。这种比较方法可以提高模型的精度。在特定的操作条件下,通过对非垂直流出池进行CFD建模,测试了不同基本形状的涡流破碎器的效率。模拟结果表明,传热和表面张力的影响可以忽略不计。在传统的垂直出流槽中,圆形板被认为是最佳的破涡器形状,而在非垂直出流池中,通过比较无量纲残余体积和流量系数,发现半挡板基本形状的最佳效率更高。与零度倒角相比,当应用20度出口管倒角设置时,半挡板断路器的流动阻力可降低34.26%。考虑到实际操作的限制,得出的结论是,半径为2.5d、高度为4/d的半挡板基本形状的破涡机构是最佳方案,适用于所有类型的储罐。与未安装断路器的情况相比,其剩余体积减少的优化效率约为56.68%。最后,基于CFD模拟,提出了一个预测一定流出速度下剩余体积的通用方程:V/d3ŞαFr0.3,其趋势与数学预测V/d3řαFr1/3一致。这种一致性证明了本文优化策略的准确性和适用性。
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来源期刊
CiteScore
7.50
自引率
5.70%
发文量
30
期刊介绍: Propulsion and Power Research is a peer reviewed scientific journal in English established in 2012. The Journals publishes high quality original research articles and general reviews in fundamental research aspects of aeronautics/astronautics propulsion and power engineering, including, but not limited to, system, fluid mechanics, heat transfer, combustion, vibration and acoustics, solid mechanics and dynamics, control and so on. The journal serves as a platform for academic exchange by experts, scholars and researchers in these fields.
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