本文描述了一个火箭发动机高深宽比冷却通道三维流动和传热分析程序。该程序是建立在抛物线化的纳维尔一斯托克斯方程基础之上的,将其流动和传热计算结果与文献中找到的测量数据进行比较,表明该程序是有效的。计算是针对实际压力为100...本文描述了一个火箭发动机高深宽比冷却通道三维流动和传热分析程序。该程序是建立在抛物线化的纳维尔一斯托克斯方程基础之上的,将其流动和传热计算结果与文献中找到的测量数据进行比较,表明该程序是有效的。计算是针对实际压力为100巴的发动机冷却通道内的流动进行的。计算出的冷却剂温升和压降值和实验结果符合良好。参数分析给出了湍流强度、壁面粗糙度、传热边界条件和近壁流动模型的影响。可以看出,本程序能够成功用于火箭发动机冷却通道内三维的流动和传热分析,它高效地利用 CPU 时间,而且用它来帮助设计现在或是将来的火箭发动机燃烧室将是很方便的。展开更多
A three-dimensional transient numerical simulation was conducted to study the pressure fluctuations in low-specific-speed centrifugal pumps. The characteristics of the inner flow were investigated using the SST k-ω t...A three-dimensional transient numerical simulation was conducted to study the pressure fluctuations in low-specific-speed centrifugal pumps. The characteristics of the inner flow were investigated using the SST k-ω turbulence model. The distributions of pressure fluctuations in the impeller and the volute were recorded, and the pressure fluctuation intensity was analyzed comprehensively, at the design condition, using statistical methods. The results show that the pressure fluctuation intensity increases along the impeller streamline from the leading edge to the trailing edge. In the impeller passage, the intensity near the shroud is much higher than that near the hub at thc inlet. However, the intensity at the middle passage is almost equal to the intensity at the outlet. The pressure fluctuation intensity is the highest at the trailing edge on the pressure side and near the tongue because of the rotor-stator interaction. The distribution of pressure fluctuation intensity is symmetrical in the axial cross sections of the volute channel. However, this intensity decreases with increasing radial distance. Hence, the pressure fluctuation intensity can be reduced by modifying the geometry of the leading edge in the impeller and the tongue in the volute.展开更多
文摘本文描述了一个火箭发动机高深宽比冷却通道三维流动和传热分析程序。该程序是建立在抛物线化的纳维尔一斯托克斯方程基础之上的,将其流动和传热计算结果与文献中找到的测量数据进行比较,表明该程序是有效的。计算是针对实际压力为100巴的发动机冷却通道内的流动进行的。计算出的冷却剂温升和压降值和实验结果符合良好。参数分析给出了湍流强度、壁面粗糙度、传热边界条件和近壁流动模型的影响。可以看出,本程序能够成功用于火箭发动机冷却通道内三维的流动和传热分析,它高效地利用 CPU 时间,而且用它来帮助设计现在或是将来的火箭发动机燃烧室将是很方便的。
基金Projects(51239005,51009072) supported by the National Natural Science Foundation of ChinaProject(2011BAF14B04) supported by the National Science&Technology Pillar Program of ChinaProject(13JDG084) supported by the Research Foundation for Advanced Talents of Jiansu University,China
文摘A three-dimensional transient numerical simulation was conducted to study the pressure fluctuations in low-specific-speed centrifugal pumps. The characteristics of the inner flow were investigated using the SST k-ω turbulence model. The distributions of pressure fluctuations in the impeller and the volute were recorded, and the pressure fluctuation intensity was analyzed comprehensively, at the design condition, using statistical methods. The results show that the pressure fluctuation intensity increases along the impeller streamline from the leading edge to the trailing edge. In the impeller passage, the intensity near the shroud is much higher than that near the hub at thc inlet. However, the intensity at the middle passage is almost equal to the intensity at the outlet. The pressure fluctuation intensity is the highest at the trailing edge on the pressure side and near the tongue because of the rotor-stator interaction. The distribution of pressure fluctuation intensity is symmetrical in the axial cross sections of the volute channel. However, this intensity decreases with increasing radial distance. Hence, the pressure fluctuation intensity can be reduced by modifying the geometry of the leading edge in the impeller and the tongue in the volute.
