助推分离对氧泵工作特性影响的模拟试验

为了研究火箭助推分离过程中,芯级液体火箭发动机氧泵入口压力快速下降对氧泵的工作特性和发动机工作性能的影响,在氢氧火箭发动机整机试车中,通过控制氧泵入口压力的方式,使氧泵逐步进入气蚀状态,开展了发动机整机状态下的氧泵气蚀研究试验,获得了氧泵气蚀状态下氧泵参数变化情况,考核了发动机经过短暂气蚀的工作特性。试验结果表明,转速升高约1800 r/min的气蚀程度,会造成氧泵流量下降7.14%,氧泵效率下降11.82%,氧泵轴向振动幅值增大约90%。氧泵在经历时间约7 s的短暂气蚀状态后,氧泵性能无明显变化,不影响发动机工作性能。

Effect of booster separation on operating characteristics of oxygen pump by simulation test

During the process of booster separating from the rocket,the rapid drop of the oxygen pump inlet pressure affects its operating characteristics and the engine performance.In order to study this question,the oxygen pump was gradually brought into a cavitation state by controlling the inlet pressure of oxygen pump in the ground hot-fire test.The cavitation test of the oxygen pump under the overall test condition was carried out,and the parameters of the oxygen pump in the cavitation state were obtained.The engine performance after a brief cavitation was evaluated.The test results show that when the cavitation occurs in the oxygen pump with the rotation rate increasing 1800 r/min,the flow rate of oxygen pump is decreased by 7.14%,the efficiency of oxygen pump is decreased by 11.82%,and the axial vibration of oxygen pump is increased by 90%approximately.After a short cavitation state of about 7 seconds,the performance of oxygen pump has no obvious change,which does not affect the engine performance.