火箭推进

采用计算流体力学方法,对某型号发动机四机并联试车推进剂供应管路所采用的分流管组件在发动机稳态工况下的推进剂流动特性进行仿真计算,并对分流管组件在发动机启动过程所产生的瞬变流动特性进行分析。计算表明,采用分流管分流的四机并联试车各发动机入口速度场与压力场均匀,可以满足发动机启动过程管道瞬变流动的要求。试验结果证明,数值计算的方法可以对推进剂供应管路设计与改进进行有效指导,对试验结果进行预测。

Under the steady-state working condition of a four-engine parallel test, the flow characteristics in the propellant supply pine with manifold assembly were simulated with CFD method. In addition, the transient flow characteristics of the manifold assembly was also analyzed during the engine startup. The calculated results show that the uniformity of velocity field and pressure field at each engine inlet in the four-engine parallel test with manifold can meet the requirements of transient flow in the pipes during engine startup. The test results show that the numerical calculation method can effectively guide the pipe design and improvement of the propellant supply system and predict the test results.

引言
1 四机分流管路简介
2 推进剂供应数学模型
3 计算结果
4 结论

图1 煤油、液氧分流管稳态压力分布及流线图<br/>Fig.1 Steady-state pressure distribution and streamline diagrams of kerosene and LOX manifolds

图1 煤油、液氧分流管稳态压力分布及流线图
Fig.1 Steady-state pressure distribution and streamline diagrams of kerosene and LOX manifolds

表1 液氧分流管出口稳态流动特性<br/>Tab.1 Steady-state flow characteristic at outlet of LOX manifold

表1 液氧分流管出口稳态流动特性
Tab.1 Steady-state flow characteristic at outlet of LOX manifold

表2 煤油分流管出口稳态流动特性<br/>Tab.2 Steady-state flow characteristic at outlet of kerosene manifold

表2 煤油分流管出口稳态流动特性
Tab.2 Steady-state flow characteristic at outlet of kerosene manifold

图2 液氧/煤油四机泵前压力特性<br/>Fig.2 Pressure characteristics before pumps of four LOX/Kerosene engines

图2 液氧/煤油四机泵前压力特性
Fig.2 Pressure characteristics before pumps of four LOX/Kerosene engines

图3 四机并联发动机启动液氧/煤油主管路流量变化率<br/>Fig.3 Flow rate changes in main pipeline of LOX/kerosene during startup of four parallel engines

图3 四机并联发动机启动液氧/煤油主管路流量变化率
Fig.3 Flow rate changes in main pipeline of LOX/kerosene during startup of four parallel engines

图4 液氧/煤油分流管路零压情况下瞬变流动特性<br/>Fig.4 Transient flow characteristic of LOX /kerosene manifold under zero pressure condition

图4 液氧/煤油分流管路零压情况下瞬变流动特性
Fig.4 Transient flow characteristic of LOX /kerosene manifold under zero pressure condition

图5 调整后液氧/煤油分流管路瞬变流动特性 <br/>Fig.5 Transient flow characteristic of regulated LOX/kerosene manifold

图5 调整后液氧/煤油分流管路瞬变流动特性
Fig.5 Transient flow characteristic of regulated LOX/kerosene manifold

[1] 李福昌.运载火箭工程[M].北京:中国宇航出版社,2002.
[2] 修泽尔D K.液体火箭发动机现代工程设计[M].朱宁昌译.北京:中国宇航出版社,2004.
[3] 张铭远.高等流体力学[M].西安:西安交通大学出版社,2006.
[4] 龙天渝.计算流体力学[M].重庆:重庆大学出版社,2007.
[5] 陶文铨.数值传热学[M].西安:西安交通大学出版社,1998.
[6] 张贵田.高压补燃液氧煤油发动机[M].北京:国防工业出版社,2005.
[7] 张国忠.管道瞬变流动分析[M].北京:石油大学出版社,1994.
[8] 张韵华.数值计算方法与算法[M].北京:科学出版社,2006.
[9] 杨永强,刘红军,徐浩海,等.补燃循环发动机强迫启动研究[J].火箭推进,2011,37(2):14-18.
[10] 陈宏玉,刘红军.补燃循环发动机推力调节过程建模与仿真研究[J].火箭推进,2014,40(1):18-24.

备注

引言

1 四机分流管路简介

2 推进剂供应数学模型

3 计算结果

4 结论

期刊信息