冲压发动机超声速进气道流动自激振荡研究

刘占生; 张云峰; 田新

冲压发动机超声速进气道流动自激振荡研究

哈尔滨工业大学能源科学与工程学院, 哈尔滨 150001

计量
- 文章访问数: 1613
- HTML浏览量: 92
- PDF量: 504
- 被引次数: 0
出版历程
- 收稿日期: 2007-08-13
- 修回日期: 2008-01-02
- 刊出日期: 2008-09-28

Research on self-excited oscillation flows in inlet of ramjet

School of Power Machinery and Engineering, Harbin Institute of Technology, Harbin 150001, China

摘要

摘要: 当冲压发动机超声速进气道工作在一定条件下时,会出现自激振荡现象.采用数值模拟方法研究了某超声速进气道结构的自激振荡现象,分析了振荡时进气道内流场的变化过程.研究表明发生自激振荡时进气道中流动产生大幅脉动,造成进气道壁板结构承受周期变化的气动载荷,载荷振荡频谱中包含多个特征频率,其与声模态频率相重合,表明自激振荡现象与声模态的相关性.
- 冲压发动机 /
- 进气道 /
- 自激振荡 /
- 声模态 /
- 流动分离 /
- 计算流体力学(CFD)
Abstract: Self-excited oscillation may arise when the inlet of ramjet is under a certain condition.This phenomenon for a supersonic inlet was numerically studied,and changes in fluid flow fields were analyzed.The results demonstrate that,in the occurrence of oscillation,the fluid flow in inlet generates large amplitude,resulting in violent periodic aerodynamic loads on ramjet wall structures.The frequency spectrum of oscillation comprises some characteristic frequencies similar with acoustic modal frequencies,implying a close relationship between acoustic modes and self-excited oscillation.
- ramjet /
- inlet /
- self-excited oscillation /
- acoustic mode /
- flow separation /
- computational fluid dynamics(CFD)

HTML

参考文献(13)

[1]	Sajben M,Bogar T J,Kroutil J C.Experimental study of flows in a two-dimensional inlet model[J].Journal of Propulsion and Power,1985,1(2):109-117.
[2]	Bogar T J,Sajben M,Kroutil J C.Characteristic frequencies of transonic diffuser flow oscillations[J].AIAA Journal,1983,21(9):1232-1240.
[3]	Liou M S,Ann A,Hankey W L,et al.Numerical simulation of a supereritical inlet flow[R].AIAA-85-1214.
[4]	Saunders J D,Keith T G Jr.Results from computational analysis of a mixed eompression supersonic inlet[R].AIAA-91-2581.
[5]	Fujiwara H,Murskami A,Watanabe Y.Numerical analysis on shock oscillation of two-dimensional external compression intakes[R].St.Louis,Missouri:32nd AIAA Fluid Dynamics Conference and Exhibit,2002,AIAA2002-2740.
[6]	Nishizawa U,Kameda M.Computational simulation of shock oscillation around a supersonic air-intake[R].San Francisco,California:36th AIAA Fluid Dynamics Conference and Exhibit,2006,AIAA 2006-3042.
[7]	Lu P J,Jain L T.Numerical investigation of inlet buzz flow[J].Journal of Propulsion and Power,1998,14(1):90-100.
[8]	尹军飞,彭成一.出口边界条件对跨音扩压器流场的影响[J].推进技术,1991,12(1):19-23.YIN Junfei,PENG Chengyi.Influence of exit-boundary conditions on transonic-diffuser flow fields[J].Journal of Propulsion Technology,1991,12(1):19-23.(in Chinese)
[9]	王世芬,李清泉.高超音速湍流分离表面热流率的脉动特性[J].力学学报,1991,23(4):426-432.WANG Shifen,LI Qingquan.Nature of the surface heat transfer fluctuation in a hypersonic separated turbulent flow[J].ACTA Mechanics Sinica,1991,23(4):426-432.(in Chinese)
[10]	彭成一,张堃元,余少志,等.跨音扩压器中的不稳定流[J].南京航空航天大学学报,1985,17(2):38-46.PENG Chenyi,ZHANG Kunyuan,Yu Shaozhi,et al.Unsteady flow in transonic diffusers[J].Journal of Nanjing University of Aeronautics and Astronautics,1985,17 (2):38-46.(in Chinese)
[11]	余少志,马家驹,丁晨,等.跨音扩压器出口流场的动态特性[J].南京航空航天大学学报,1985,17(2):47-55.YU Shaozhi,MA Jiaju,Ding Cheng,et al.Dynamic characteristics of the flow field at the exit of transonic diffusers[J].Journal of Nanjing University of Aeronautics and Astronautics,1985,17(2):47-55.(in Chinese)
[12]	余少志,彭成一,尹军飞.跨音扩压器中激波附面层相互作用[J].南京航空航天大学学报,1985,17(2):56-69.YU Zhaozhi,PENG Chengyi,YIN Junfei.Shock wave/ boundary layer interaction in a transonic diffuser[J].Journal of Nanjing University of Aeronautics and Astronautics,1985,17(2):56-69.(in Chinese)
[13]	Carroll B F,Dutton J C.Characteristics of multiple shock wave/turbulent boundary-layer interactions in rectangular ducts[J].Journal of Propulsion and Power,1990,6(2):186-193.