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液体喷嘴动态特性数值模拟
引用本文:杨立军,张向阳,高芳,张振鹏.液体喷嘴动态特性数值模拟[J].航空动力学报,2004,19(6):866-872.
作者姓名:杨立军  张向阳  高芳  张振鹏
作者单位:北京航空航天大学,宇航学院,北京,100083
基金项目:863基金资助项目(2002AA726022)
摘    要:对直流、离心喷嘴进行了理论分析,采用"频率法"对直流和离心喷嘴的动态特性进行了数值模拟,所得结果表明:增加振荡频率会导致直流和离心喷嘴流量的振幅降低和相移增大,而增大压降则结果相反;在相同工况下,当直流喷嘴增大长径比或离心喷嘴增大几何特性时均会导致振幅降低和相移增大,离心喷嘴喷口长度增大导致相移增大,而对振幅无明显影响。此结果与国外研究结果符合较好,并为进一步开展喷嘴动力学研究奠定了基础。

关 键 词:航空、航天推进系统  直流喷嘴  离心喷嘴  动态特性  数值模拟
文章编号:1000-8055(2004)06-0866-07
收稿时间:2003/11/13 0:00:00
修稿时间:2003年11月13

Numerical Simulation of Liquid Injector Dynamics
YANG Li-jun,ZHANG Xiang-yang,GAO Fang and ZHANG Zhen-peng.Numerical Simulation of Liquid Injector Dynamics[J].Journal of Aerospace Power,2004,19(6):866-872.
Authors:YANG Li-jun  ZHANG Xiang-yang  GAO Fang and ZHANG Zhen-peng
Institution:School of Astronautics,Beijing University of Aeronautics and Astronautics,Beijing100083,China;School of Astronautics,Beijing University of Aeronautics and Astronautics,Beijing100083,China;School of Astronautics,Beijing University of Aeronautics and Astronautics,Beijing100083,China;School of Astronautics,Beijing University of Aeronautics and Astronautics,Beijing100083,China
Abstract:In order to study the dynamic characteristics of liquid rocket engine injectors,theoretical analysis has been carried out for the plane orifice and centrifugal injectors."Frequency Method" was used for the numerical simulation of the injector dynamics.The results show that with the increase of pulse frequency,the flux swing of the plane orifice and centrifugal injectors decreases and the phase shift increases.With the increase of pressure,the flux swing increases and the phase shift decreases.Under the same condition,with the increase of the plane orifice injector's length or the geometric characteristics of centrifugal injectors,the swing decreases and the phase shift increases.With the increase of the spout length of centrifugal injectors,the phase shift increases while the swing is not affected remarkably.These results agree well with foreign investigations and establish the basis for further study.
Keywords:aerospace propulsion system  plane orifice injector  centrifugal injector  dynamics  numerical simulation
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