火箭推进2018，Vol.44Issue(2)：10-17,8.
推力室头部最优气膜参数研究
Study on optimal gas film parameters of near-injection region in thrust chamber
高兴峰 1张建伟 1孙冰 1王太平1
作者信息
- 1. 北京航空航天大学宇航学院,北京100191
- 折叠
摘要
Abstract
A three-dimensional numerical simulation of the gas-gas combustion chamber with the multi-element injector with gas film cooling was investigated to obtain the optimal parameters that affect the gas film cooling of the near-injection region in the thrust chamber of the hydrogen-oxygen rocket en-gine.In the numerical model,the standard k-ε model and the eddy-dissipation concept model are used to simulate the turbulence and combustion process respectively.The orthogonal test method is used to ana-lyze the effect of the different film parameters.The analysis results show that the gas film can reduce the wall temperature of combustor in the near-injection region effectively and homogenize the wall temperature distribution,play a role in thermal protection of the injector head in a certain extent,and flow rate ratio of the gas film has greater influence on the cooling efficiency and the uniformity in the circumferential di-rection in comparison with the structure of the gas film inlet.The more homogeneous cooling distribution of the gas film can be achieved by selecting the appropriate gas film flow parameter and gas film inlet structure.The injection of the film has a great influence on the combustion efficiency,especially for the structural parameters of the film inlet.The results obtained in this study could be used to provide a refer-ence for the design of gas film cooling.关键词
推力室/数值模拟/正交试验法/冷却效率/燃烧效率Key words
thrust chamber/numerical simulation/orthogonal test method/cooling efficiency/com-bustion efficiency分类
航空航天引用本文复制引用
高兴峰,张建伟,孙冰,王太平..推力室头部最优气膜参数研究[J].火箭推进,2018,44(2):10-17,8.
