轨控发动机喉部高温问题分析与抑制方法  

Analysis and Suppression Methods of High Temperature Problems in the Throat of Orbit Controlled Engine

作　　者：李剑锐 苏航 刘昌国 陈泓宇 叶奕翔 LI Jianrui;SU Hang;LIU Changguo;CHEN Hongyu;YE Yixiang(Shanghai Institute of Space Propulsion,Shanghai 201112,China;Shanghai Engineering Research Center of Space Engine,Shanghai 201112,China)

机构地区：[1]上海空间推进研究所,上海201112 [2]上海空间发动机工程技术研究中心,上海201112

出　　处：《深空探测学报（中英文）》2024年第2期132-140,共9页Journal Of Deep Space Exploration

摘　　要：针对发动机在稳态试车点火过程中出现的喉部单侧局部高温和焊缝温度阶跃升高的现象,导致身部涂层寿命衰减及产生了局部应力,严重危害发动机可靠性的问题,采用CFD仿真对头部喷注器结构建模,结合流阻数学模型进行优化分析,优化流道内的分配结构,实现降低喷注流阻的同时改善撞击对流量造成的不均匀性问题,并通过调整撞击参数,优化燃烧组织和边区液膜冷却方案,优化边区混合比,同时降低了喉部温度和周向温差。改进后的发动机经过试验验证,在性能不变的情况下使高空模拟热试车喉部温度由近1500℃下降至1270℃,头身焊缝处温度由520℃下降至310℃,发动机身部周向温度差控制在50℃以内,有效地解决了发动机喉部的高温问题,提升了发动机的使用寿命和工作可靠性。Based on the phenomenon of single-side local high temperature of throat and high jump of weld temperature during steady-state test ignition of the engine.which seriously endangers the reliability of the engine,CFD simulation was used to model the structure of the head injector and optimize the distribution structure in the flow channel combined with the flow resistance mathematical model.To achieve the reduction of jet flow resistance and improve the non-uniformity of flow caused by impact,and optimize the combustion structure and liquid film cooling scheme in the side zone by adjusting the impact parameters,optimize the mixing ratio in the side zone,and reduce the throat temperature and circumferential temperature difference.The improved engine has been verified by experiments.Under the condition of unchanged performance,the temperature of the high-altitude simulated thermal test throat was reduced from nearly 1500℃ to 1270℃,the temperature at the headbody weld was reduced from 520℃ to 310℃,and the temperature difference of the engine body was controlled within 50℃,which effectively solved the problem of high temperature in the engine throat.The service life and reliability of the engine were improved.

关 键 词：液体火箭发动机 双组元 身部高温 可靠性 

分 类 号：V343[航空宇航科学技术]