运载火箭增压管路随机性压力跳变机理及试验验证

Abnormal Pressure Jump Mechanism and Test Validation in Rocket Pressurized Pipeline

针对常规在役液体运载火箭一级燃增压路入口的随机性压力跳变现象,通过理论分析、数值仿真及试验验证,提出了燃增压路内存在的两种稳定流型:正常流型和螺旋流型。在随机性扰动的激励下,管路内两种流型发生突变,局部流阻增加,增压管路入口压力产生跳变现象,从机理上复现了燃增压路的随机性压力跳变现象。在此基础上,提出了增加隔板结构抑制燃增压路压力跳变现象的改进方案,试验结果表明,该隔板方案可有效消除燃增压路中的压力跳变现象,也从侧面验证了螺旋流流型的存在。

Aimed at the random pressure jump phenomena at the inlet of first stage self-pressurization pipeline in the conventional liquid launch vehicle in service,two stable flow patterns including normal flow pattern and spiral flow pattern are proposed via theoretical analysis,numerical simulation and experimental verification.Under the excitation of random disturbance,the two flow patterns may transfer each other,which make the local flow resistance increase,and the inlet pressure of the pressurized pipeline abnormal rise.On this basis,an improved scheme of adding baffles suppressing the pressure jump phenomena is proposed.The test results indicate that the baffles can effectively eliminate the pressure jump phenomena in rocket pressurized pipeline,and also verify the existence of spiral flow pattern from the side.