摘要
通过三维稳态数值模拟和正交实验研究方法,系统分析了不同结构参数的消旋肋片对涡轮泵平衡活塞内部流动特性及轴向力的影响规律。选取某液体火箭发动机涡轮泵的平衡活塞流域作为研究对象,进行三维稳态数值模拟,分析了消旋肋片对平衡活塞内部流动特性的影响;设计正交实验方案,通过调整消旋肋片的宽度、高度及数量,进一步评估了各参数对轴向力影响的差异性。研究结果表明:消旋肋片的加入显著影响了涡轮泵平衡活塞内部流动特性;引入消旋肋片后,平衡活塞模型内部流动变得更加复杂,在动静圆盘间隙出现了更多的涡,增加了能量耗散,进而引发平衡活塞内部压力变化,轴向力明显改变,泄漏通道内的轴向力降低幅度可达14.3%;在选取的消旋肋片结构参数中,按照对轴向力的影响大小从高到低依次为消旋肋片的宽度、高度及数量,且前两者对结果的极差值分别为消旋肋片数对应结果的4.6倍和3.5倍。该研究通过消旋肋片结构参数设计改善了平衡活塞的工作特性,从而提高涡轮泵运行的稳定性,为液体火箭发动机涡轮泵性能优化提供了一定的参考。
Through three-dimensional steady-state numerical simulations and orthogonal experimental design,this study systematically investigates the influence of anti-swirl ribs with varying structural parameters on flow characteristics and axial force within turbopump balance pistons.The flow domain of the turbopump balance piston in a liquid rocket engine is selected as the research object for 3D steady-state numerical simulation,revealing the impact of anti-swirl ribs on internal flow patterns.An orthogonal experimental scheme is designed to evaluate the differential effects of rib width,height,and quantity on axial force.The introduction of anti-swirl ribs significantly alters the internal flow characteristics of the turbopump balance piston.After implementing anti-swirl ribs,the internal flow patterns become more complex,with increased vortex generation in the rotor-stator disk gaps that enhances energy dissipation.This subsequently modifies the internal pressure distribution,leading to notable changes in axial force-achieving up to a 14.3%reduction in axial force within the leakage channel.Among the selected structural parameters of anti-swirl ribs,their influence on axial force,ranked from highest to lowest,is as follows:width,height,and quantity.The first two parameters show ranges of 4.6 times and 3.5 times the corresponding results for the quantity of anti-vortex ribs,respectively.Through optimized anti-swirl rib parameter design,this study improves the operational characteristics of balance pistons,thereby enhancing turbopump stability.The findings provide valuable references for performance optimization of liquid rocket engine turbopumps.
作者
杨铁恒
许开富
金路
郑旭
孙中国
席光
YANG Tieheng;XU Kaifu;JIN Lu;ZHENG Xu;SUN Zhongguo;XI Guang(School of Energy and Power Engineering,Xi’an Jiaotong University,Xi’an 710049,China;Xi’an Aerospace Propulsion Institute,Xi’an 710100,China)
出处
《西安交通大学学报》
北大核心
2025年第7期46-55,共10页
Journal of Xi'an Jiaotong University
关键词
涡轮泵
平衡活塞
轴向力
消旋肋片
turbopump
balance piston
axial force
swirl brake
作者简介
杨铁恒(1997-),男,硕士生;通信作者:孙中国,男,教授,博士生导师。
