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作 者:刘万龙[1] 朱昊伟 赵宏[1] 胡旭坤[1] 李茂[1] Liu Wan-long;Zhu Hao-wei;Zhao Hong;Hu Xu-kun;Li Mao(Beijing Institute of Aerospace Testing Technology,Beijing,100076)
出 处:《导弹与航天运载技术》2021年第2期54-59,共6页Missiles and Space Vehicles
摘 要:为了研究高压缩比单级环形引射器的性能,基于一维管流的基本理论对环形引射器进行设计,分别加工了开缝及不开缝环形引射器。在零负载情况下,试验测得不开缝引射器临界启动压力为1.127MPa,极限真空压力为6294Pa,压缩比约为16.1;试验测得开缝引射器临界启动压力1.181MPa,极限真空压力为984Pa,压缩比约为103,开缝后压缩比提升了6.4倍左右。相比不开缝引射器,开缝引射器可以大幅降低零负载情况下的真空压力,但启动压力也略有提升,试验表明在0.1MPa以内。启动后引射器真空压力与入口压力之间有接近线性的递增关系。目前的试验表明,通过合理开缝,可以通过单级环形引射器实现1000Pa以下的极限真空,可以应用在大推力氢氧火箭发动机启动前30km高空模拟。In order to study the performance of high compression ratio single-stage annular ejector,an annular ejector is designed based on the basic theory of one-dimensional tube flow,and the slotted and normal annular ejectors are made.Under zero load conditions,the critical start pressure of the normal ejector is 1.127 MPa in tests,and the ultimate vacuum pressure is 6294 Pa.The compression ratio of the normal ejector is approximately 16.1.The critical starting pressure of the slotted ejector is 1.181 MPa in the tests,and the ultimate vacuum pressure is 984 Pa.The compression ratio of the slotted ejector is about 103.The compression ratio of the annular ejector is increased by 6.4 times after been slotted.Compared with the normal annular ejector,the vacuum pressure can be greatly reduced with the slotted annular ejector,and the starting pressure was just slightly improved.The tests showed that the improved starting pressure was less than 0.1 MPa.There is a near linear relationship between the ejector vacuum pressure and the inlet pressure after startup.The current tests show that the ultimate vacuum below 1000 Pa can be achieved by a single-stage annular ejector after been slotted,which can be applied to the 30 km high altitude simulation before the start of the large thrust hydrogen-oxygen rocket engine.
分 类 号:V416.8[航空宇航科学与技术—航空宇航推进理论与工程]
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