火箭推进

在涡轮泵启动物理模型理论分析的基础上,编写仿真程序对启动过程进行分析。搭建了涡轮泵启动性能试验台,采用某型火箭发动机涡轮泵进行试验验证。仿真结果表明该模型满足涡轮泵启动特性研究的要求,试验结果表明该试验方案适合进行涡轮泵启动性能试验研究,可用于研究涡轮泵启动过程中涡轮、泵、机械密封、轴承等重要零组件的性能。

For the turbopump in liquid rocket engine, a simulation program was compiled to analyze its start-up process based on the theoretical analysis.Moreover, an experimental rig for the start-up performance of turbopump was built and the turbopump in a certain type of engine was tested for verification.The simulation results show that the model meets the study requirements of the start-up process.The experimental results show that the experimental scheme is suitable for the performance study of turbopump start-up, and can be used in the investigation of turbine, pump, mechanical seal, bearing and other important components.

引言
1 试验系统方案及要求
2 涡轮泵启动数学模型
3 仿真及试验结果分析
4 结论

图1 涡轮泵启动性能试验方案简图<br/>Fig.1 Test diagram of turbopump start-up performance

图1 涡轮泵启动性能试验方案简图
Fig.1 Test diagram of turbopump start-up performance

图2 冲击式涡轮叶片进出口速度示意图<br/>Fig.2 Schematic diagram of inlet and outlet velocity for impact turbine blade

图2 冲击式涡轮叶片进出口速度示意图
Fig.2 Schematic diagram of inlet and outlet velocity for impact turbine blade

图3 涡轮泵转速随气瓶初始压力变化曲线<br/>Fig.3 Turbopump speed for different initial bottle pressures

图3 涡轮泵转速随气瓶初始压力变化曲线
Fig.3 Turbopump speed for different initial bottle pressures

图4 涡轮泵转速随气瓶容积变化曲线<br/>Fig.4 Turbopump speed for different bottle volumes

图4 涡轮泵转速随气瓶容积变化曲线
Fig.4 Turbopump speed for different bottle volumes

图5 涡轮泵转速随进气阀门流通面积变化曲线<br/>Fig.5 Turbopump speed for different flow areas of inlet valve

图5 涡轮泵转速随进气阀门流通面积变化曲线
Fig.5 Turbopump speed for different flow areas of inlet valve

图6 喷嘴入口压力和火药启动器腔压曲线<br/>Fig.6 Pressure comparison between nozzle inlet and cartridge starter cavity

图6 喷嘴入口压力和火药启动器腔压曲线
Fig.6 Pressure comparison between nozzle inlet and cartridge starter cavity

图7 涡轮泵转速对比<br/>Fig.7 Comparison of turbopump rotation speeds

图7 涡轮泵转速对比
Fig.7 Comparison of turbopump rotation speeds

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备注

引言

1 试验系统方案及要求

2 涡轮泵启动数学模型

3 仿真及试验结果分析

4 结论

期刊信息