基于混合正交法的环喉式膨胀偏流喷管性能影响因素研究  

Investigation of influence of design factors on annular throat expansion-deflection nozzle performance based on mixed orthogonal method

作　　者：王革[1] 张渴欣 周博成 陈磊 关奔[1] 汪根来 WANG Ge;ZHANG Kexin;ZHOU Bocheng;CHEN Lei;GUAN Ben;WANG Genlai(Collage of Aerospace and Civil Engineering,Harbin Engineering University,Harbin 150001,China;The 41st institute of the Sixth Academy of CASIC,Hohhot 010076,China)

机构地区：[1]哈尔滨工程大学航天与建筑工程学院,哈尔滨150001 [2]中国航天科工集团有限公司第六研究院41所,呼和浩特010076

出　　处：《固体火箭技术》2023年第3期410-418,共9页Journal of Solid Rocket Technology

摘　　要：利用混合正交法设计数值模拟实验对环喉式膨胀偏流喷管(ATEDN)的工作过程进行研究,以获得ATEDN在不同工作模态的流场特征并分析入口压力、扩张比和塞锥基底半径三个影响因素共同作用下喷管性能的变化规律及各因素对喷管性能影响的显著性。采用FLUENT商用软件对ATEDN在0~31 km高度范围内的工作状态进行模拟。模拟结果表明,ATEDN在不同工作高度下存在开放-固壁反射、开放-自由边界反射和闭合三种基本工作模态。根据喷管流动经历的不同工作模态特征,将喷管的工作过程进行分类,具有不同工作过程的喷管推力性能存在显著差异。结果对比发现,在所选的参数水平下,塞锥基底半径是影响高度积分平均比冲的最显著因素,其次是扩张比,入口压力影响最小。随着喷管扩张比的增加,高度积分平均比冲降低;随着喷管入口压力和塞锥基底半径增加,高度积分平均比冲增加。The mixed orthogonal method was applied to design numerical simulation experiment in order to investigate the operation states of the annular throat expansion-deflection nozzles(ATEDN).Flow features of the ATEDN under different operating modes were obtained,the nozzle performance under different nozzle inlet pressures,expansion ratios,and pintle base radiius were analyzed,and the contribution significance of each design factor was evaluated.The FLUENT commercial software was used to simulate the ATEDN operating states within an altitude of 0~31 km.The results show that the ATEDN at different working altitudes has three basic operating modes,namely,the open-wall reflection mode,the open-free boundary reflection mode,and the closed mode.These modes are used to divide the present simulated cases into different operating processes,each of which has distinct nozzle performance.It is found that,under the present parameter levels,the pintle base radius is the the most significant factor affecting the nozzle altitude-integral average specific impulse,the second is the expansion ratio,and the weakest is the nozzle inlet pressure.With the increase of the nozzle expansion ratio,the altitude-integral average specific impulse decreases,while with the increase of the nozzle inlet pressure and the pintle base radius,the altitude-integral average specific impulse also increases.

关 键 词：环喉式膨胀偏流喷管 混合正交法 平均比冲 数值模拟 

分 类 号：V435[航空宇航科学与技术—航空宇航推进理论与工程]