航天推进技术研究院主办
[1]王玉峰,杨宝娥.超声速进气道喘振的机理研究[J].火箭推进,2008,34(01):17-22.
Wang Yufeng,Yang Baoe.Study of the buzz mechanism of supersonic inlets[J].Journal of Rocket Propulsion,2008,34(01):17-22.
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Wang Yufeng,Yang Baoe.Study of the buzz mechanism of supersonic inlets[J].Journal of Rocket Propulsion,2008,34(01):17-22.
超声速进气道喘振的机理研究
《火箭推进》[ISSN:1672-9374/CN:CN 61-1436/V]
卷:
34
期数:
2008年01期
页码:
17-22
栏目:
研究与设计
出版日期:
2008-02-29
- Title:
- Study of the buzz mechanism of supersonic inlets
- Keywords:
- inlet; buzz; separate eddy
- 分类号:
- V211.3
- 文献标志码:
- A
- 摘要:
- 应用数值模拟方法对中心锥中心进气混压武进气道的喘振现象进行了研究。在 数值计算的基础上。根据进气道出口截面每个网格点的压力、密度、速度等参数计算了进气 道喘振过程中流量系数和总压恢复系数随时间的变化情况。同时给出了在喘振过程中激波振 荡的振幅、频率、对应的波系图案。并根据进气道头部分离涡的发展情况以及进气道内通道 中状态参数的变化情况对喘振产生的机理进行了分析．认为进气道头部分离涡对喘振的产生 起关键的作用。
- Abstract:
- In this paper buzz of a supersonic mixed-compression inlet with conic multi--compression is studied with numerical method．The periodical change of the pressure recovery and mass flow ratio is calculated on the base of the flow field result．The frequency，amplitude and shock wave train of the terminal shock wave oscillation during buzz process were analyzed．The development of the separated eddy on the compression surface works as a critical factor in inlet buzz based on the analysis of inlet flow field and state parameters．
参考文献/References:
[1]刘兴洲．飞航导弹动力装置(上)[M]．北京：宇航出版社，
1992．
[2]Goldsmith E L Shock Oscillation Ahead of Centrebody
brakes at Supersonic Spocd[R]．AIAAl952-2477．
[3]Sterbentz W H．Cfitefiom for Prediction and Control of
Ramjet Flow Flow Puhation[R]．NASA TN 1955-3506．
[4]Pong Jeu Lu,Ling Tzong Jain．Numerical Investigation of
Inlet Buzz now Flow[J]．Journal of Propulsion and Power,1998,
14(11)：90-100．
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备注/Memo
收稿日期：2007-06-26；修回日期：2007—11—10。 作者简介：王玉峰(198p)，男，硕士，研究领域为发动机系统设计。
更新日期/Last Update:
1900-01-01