摘要
基于Fluent平台,采用组分输运模型和有限速率/涡破碎燃烧模型对喷管扩张段补充燃烧进行数值模拟。研究了空气注入量、空气入射角度和空气入射位置对喷管推力增益的影响。结果表明,随着空气注入量的增加,推力增大;随着空气入射角度增加,推力先增大后减小;一定范围内,空气入射位置对推力增益影响不大。
The combustion of Solid propellant is lean oxygen combustion,and the gas contains a large number of combustible components. In order to use this part of energy,the air is added in the nozzle expansion section to supplement the combustion. Based on the Fluent platform,the numerical simulation of the combustion was carried out by using the component transport model and the Finite-Rate/Eddy-Dissipation model. The effects of air injection rate,incident angle and incident position on the thrust gain are studied. With the increase of air injection amount,the thrust increased. The thrust increases first and then decreases with the increase of the incident angle. In a certain range,the air incident position has little effect on the thrust gain.
出处
《兵器装备工程学报》
CAS
2017年第12期292-296,共5页
Journal of Ordnance Equipment Engineering
关键词
固体火箭发动机
喷管
补充燃烧
推力
数值模拟
solid rocket motor
nozzle
supplemental combustion
thrust
numerical simulation
