基于橇载喷管背压控制的引射装置设计与研究
Design and research of ejector based on skid mounted nozzle back pressure control
张晨辉 1谢波涛 1王宝林 1杨洋1
作者信息
- 1. 中国兵器工业试验测试研究院,陕西华阴 714200
- 折叠
摘要
为解决火箭橇试验橇载喷管背压过高的问题,验证引射装置设计的可行性,建立了二维引射性能预估模型,利用Fluent软件,并采用k-ε湍流模型,研究引射装置及其关键设计参数对喷管内部流场的影响,揭示了试验装置内外流场掺混机理.数值分析结果表明:引射装置适用于大扩张比、低Ma数试验工况;引射装置总压、引射流量越大,引射效应越明显,引射装置与喷管尾端的距离、引射角度大小与引射效率呈负相关,设计中应保证引射装置燃气/空气流量比为0.75 以上,引射位置在中部和后部时激波前的试验面积分别增加了0.42、0.75 m2;引射装置的加入使得试验段平均马赫数由2.6 提升至3.3,均匀度提高约72%.
Abstract
In order to solve the problem of high back pressure in the rocket sled test skid nozzle and verify the feasibility of the ejector design,a two-dimensional ejector performance prediction model was established.It used the FLUENT software and k-ε turbulence model to study the influence of the ejector and its key design parameters on the internal flow field of the nozzle,and revealed the mixing mechanism of the internal and external flow field of the test device.The numerical analysis results show that the ejector is suitable for the test conditions of large expansion ratio and low Ma number;With the increase of the ejector total pressure and ejection flow of the engine,the ejection effect is more obvious.The distance between the ejector and nozzle end and the size of the ejection angle are negatively correlated to the ejection efficiency.It should be ensured that the ejector gas/air flow ratio is more than 0.75 in the design,and test area before the shock wave in the middle and rear is increased by 0.42 m2 and 0.75 m2;After the ejector is added in the test system,the average Mach number of the test section is increased from 2.6 to 3.3,and the uniformity is increased by about 72% .
关键词
火箭橇/喷管/引射装置/扩张比Key words
rocket sled/nozzle/ejector/expansion ratio引用本文复制引用
基金项目
国防科技创新特区项目(20-163-16-ZD-005-007-01)
出版年
2024
NETL
NSTL
维普
万方数据