固体火箭技术2024，Vol.47Issue(2)：164-172,9.DOI:10.7673/j.issn.1006-2793.2024.02.003
超音速分离线喷管大摆角状态下化学烧蚀动态仿真
Chemical ablation dynamic simulation of supersonic split line nozzle with large deflection angle
廖栩锋 1田维平 2王健儒 2曹涛锋1
作者信息
- 1. 西安航天动力技术研究所,西安 710025
- 2. 航天动力技术研究院,西安 710025
- 折叠
摘要
Abstract
Aiming at the wall regression caused by chemical ablation in the supersonic split line nozzle with large deflection an-gle,a corresponding dynamic simulation model has been established based on the dynamic mesh technology,which realize prediction of the nozzle chemical ablation rate under different combustion chamber conditions.The throat ablation rate of 0.048 6 mm/s was ob-tained by means of the preliminary steady-state calculation,5.67%higher than the experimental result,verifying reasonableness of simulation setup.Then the state result was used as the initial field of transient calculation to carry out the corresponding dynamic simulation calculation of nozzle's chemical ablation.The vector angular amplification factor of the nozzle is reduced by 0.42%in 0.5 s simulation time due to the wall regression,and the most serious ablation position of nozzle is near the split line structure on the lower sidewall of the symmetry plane due to the obstruction of the gas flow,and the maximum ablation rate is 0.074 5 mm/s.Increas-ing the combustion chamber pressure or temperature will lead to a decrease in the ratio of ablation rate between the back and front sidewall of split line at the same circumferential position.For the less varied profile near the split line,this ratio is decreased by a-bout 10%with the increase of combustion chamber pressure from 5.5 MPa to 7.5 MPa and by about 15%with the increase of tem-perature from 3200 K to 3600 K.关键词
超音速分离线喷管/化学烧蚀/动网格/数值仿真Key words
supersonic split line nozzle/chemical ablation/dynamic mesh/numerical simulation分类
航空航天引用本文复制引用
廖栩锋,田维平,王健儒,曹涛锋..超音速分离线喷管大摆角状态下化学烧蚀动态仿真[J].固体火箭技术,2024,47(2):164-172,9.
