航天推进技术研究院主办
[1]胡海峰,高新妮,凌前程,等.火箭发动机喷管分离流动仿真分析[J].火箭推进,2014,40(06):21-26.
HU Hai-feng,GAO Xin-ni,LING Qian-cheng,et al.Simulation analysis on separation flow in rocket engine nozzle[J].Journal of Rocket Propulsion,2014,40(06):21-26.
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HU Hai-feng,GAO Xin-ni,LING Qian-cheng,et al.Simulation analysis on separation flow in rocket engine nozzle[J].Journal of Rocket Propulsion,2014,40(06):21-26.
火箭发动机喷管分离流动仿真分析
《火箭推进》[ISSN:1672-9374/CN:CN 61-1436/V]
卷:
40
期数:
2014年06期
页码:
21-26
栏目:
研究与设计
出版日期:
2014-12-29
- Title:
- Simulation analysis on separation flow in rocket engine nozzle
- Keywords:
- large expand ratio nozzle; flow separation; wavelet analysis; FEM
- 分类号:
- V434-34
- 文献标志码:
- A
- 摘要:
- 采用数值方法研究在分离状态下的最大推力喷管流动状态，讨论了不同湍流模型对分离流动的影响，在此基础上详细分析了喷管流动中出现气流分离模态由自由激波（FSS）到受限激波(RSS)的变化情况。在稳态仿真基础上开展非稳态分析，并综合小波分析、结构有限元方法分析了侧向载荷影响。研究结果表明，喷管内压强脉动为低频脉动，该脉动频率范围与喷管固有频率有交叠，可为后续的喷管气流分离侧向载荷分析及验证试验提供基础。
- Abstract:
- Flow status of the large expand ratio rocket engine nozzle is studied with numerical method. The influence of the different RANS turbulence models on separation flow is discussed. Based on this, the variation of flow separation modal from free shock separation (FSS) to restricted shock separation (RSS) occurred in the nozzle is analyzed in detail. The unsteady-state analysis is carried out on the basis of steady-state simulation. The effect of lateral load is also analyzed in combination with the wavelet analysis and FEM. The research result shows that the pressure intensity pulsation in the nozzle is low-frequency one, whose frequency range has resonance with inherent frequency of the nozzle. The conclusion laid a foundation for the subsequent analysis and verification test of the lateral load of flow separation in the nozzle.
参考文献/References:
[1]FREY M, HAGEMANN G. Status of flow separation pre-diction in rocket nozzles[C]//34th AIAA/ASME/SAE /ASEE Joint Propulsion Conference & Exhibit. Cleve- land, Oh, USA: AIAA, 1998: 13-15.
[2]SMALLEY K B, BROWN A M, RUF J. Flow separation side-loads excitation of rocket nozzle FEM[C]//48th AIAA/ASME/ASCE/AHS/ASC Structures, Structural Dynamics, and Materials Conference. Honolulu, Hawaii, USA: AIAA, 2007: 23-26.
[3]TERHARD M T, HAGEMANN G, FREY M. Flow separation and side-load behavior of truncated ideal rocket nozzles[C]//35th AIAA/ASME/SAE/ASEE Joint Propulsion Conference and Exhibit. Salt Lake City, UT, USA: AIAA, 1999: 8-11.
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[5]林震, 王长辉, 刘宇, 许晓勇. 喷管分离流动及其侧向载荷[J]. 北京航空航天大学学报, 2010, 36(3): 307-310.
[6]吴朋朋, 杨月诚, 高双武, 等. 大面积比喷管侧向载荷流固耦合数值仿真[J]. 弹箭与制导学报, 2013, 33(2): 75- 78.
[7]MARTELLI E, NASUTI F, ONOFRI M. Numerical calculation of FSS/RSS transition in highly overexpanded rocket nozzle flows[J]. Shock Waves, 2010, 20: 139-146.
[8]LIJO V, KIM H D, SETOGUCHI T, et al. Numerical simulation of transient flows in a rocket propulsion nozzle[J]. International Journal of Heat and Fluid Flow, 2010, 31: 409-417.
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[10]STLUND J. Flow processes in rocket engine nozzles with focus on flow separation and side-loads[R]. [S.l.]: TRITAMEK, 2002.
[11]王艺杰, 鲍廷, 杜佳佳. 固体火箭发动机喷管分离流流动数值模拟及实验研究[J]. 固体火箭技术, 2010, 33(4): 406-408.
备注/Memo
收稿日期：2014-08-13；修回日期：2014-08-29 作者简介：胡海峰（1986—），男，工程师，研究领域为液体火箭发动机设计
更新日期/Last Update:
1900-01-01