不同摆角超声速分离线喷管烧蚀数值研究  

Numerical investigation of supersonic split line nozzle ablation with different deflection angles

作　　者：廖栩锋 田维平[2] 王健儒[2] 曹涛锋 LIAO Xufeng;TIAN Weiping;WANG Jianru;CAO Taofeng(Institute of Xi’an Aerospace Solid Propulsion,Xi’an 710025,China;Academy of Aerospace Solid Propulsion Technology,Xi’an 710025,China)

机构地区：[1]西安航天动力技术研究所,陕西西安710025 [2]航天动力技术研究院,陕西西安710025

出　　处：《推进技术》2024年第11期152-160,共9页Journal of Propulsion Technology

摘　　要：建立了适用于超声速分离线喷管的三维烧蚀仿真方法,与试验结果对比验证了其有效性,对不同摆角的喷管烧蚀状况进行了数值仿真。结果表明,由于喷管型面改变,分离线附近烧蚀率出现骤升骤降的复杂变化。分离线前侧壁面大部分位置烧蚀率受摆角影响较小,仅下侧点位置附近由于燃气流动受阻烧蚀率随摆角增大而增大,当摆角为5°时,为喷管整体烧蚀最严重区域,烧蚀率为79.4μm/s。分离线后侧壁面烧蚀率受摆角影响较大,且整体高于前侧。在分离线下游上侧边界线,烧蚀率会快速出现一个峰值,且出现位置随摆角增大后移,从0°的59.7 mm后移至5°的65.3 mm处。摆角为5°时,由于下侧激波切割了流场,导致了上侧边界线x=130 mm燃气流动出现分离现象,烧蚀率在此处回升到5.8μm/s。A 3D ablation simulation method suitable for supersonic split line nozzle was established,and its validity was verified by comparing it with the test results,then numerical simulation of the nozzle ablation with different deflection angles was carried out.Due to the change of nozzle wall contiguity,there is a complex change of sudden rise and fall of the ablation rate near the split line.The ablation rate of most positions on the front side of the split line is less affected by the deflection angle,and only the ablation rate at the lower sidewall in symme⁃try plane increases with the deflection angle’s increase due to the obstruction of the gas flow.And when the de⁃flection angle is 5°,the position is the most serious region of the overall nozzle’s ablation and the ablation rate is 79.4μm/s.The ablation rate at the back sidewall of the split line is more affected by the deflection angle and is higher than that at the front sidewall in the whole.At the upper boundary polyline downstream of the split line,the ablation rate will quickly appear a peak,and the position with the increase of the deflection angle shifts back from 59.7 mm at 0°to 65.3 mm at 5°.At the deflection angle of 5°,the ablation rate rises back to 5.8μm/s here due to the separation of the gas flow at the upper boundary polyline x=130 mm caused by the cutting of the flow field by the shock wave at the lower side.

关 键 词：固体火箭发动机 超声速分离线喷管 烧蚀 摆动角度 流动特性 

分 类 号：TJ763[兵器科学与技术—武器系统与运用工程] V435[航空宇航科学与技术—航空宇航推进理论与工程]