航天推进技术研究院主办
[1]万冰,陈军,白菡尘.支板式RBCC零速与非零速条件引射特性分析[J].火箭推进,2022,48(06):74-84.
WAN Bing,CHEN Jun,BAI Hanchen.Analysis on the ejecting characterictics of a struct-based RBCC at zero speed and non-zero speed condition[J].Journal of Rocket Propulsion,2022,48(06):74-84.
点击复制
WAN Bing,CHEN Jun,BAI Hanchen.Analysis on the ejecting characterictics of a struct-based RBCC at zero speed and non-zero speed condition[J].Journal of Rocket Propulsion,2022,48(06):74-84.
支板式RBCC零速与非零速条件引射特性分析
《火箭推进》[ISSN:1672-9374/CN:CN 61-1436/V]
卷:
48
期数:
2022年06期
页码:
74-84
栏目:
目次
出版日期:
2022-12-25
- Title:
- Analysis on the ejecting characterictics of a struct-based RBCC at zero speed and non-zero speed condition
- 文章编号:
- 1672-9374(2022)06-0074-11
- Keywords:
- RBCC ejection process flow structure evolvement speed condition mass flow rate control mechanism
- 分类号:
- V235.21
- 文献标志码:
- A
- 摘要:
- 为获得来流速度条件对RBCC发动机引射特性的影响,采用数值模拟方法研究了支板式RBCC构型在亚声速范围的引射流场特性。结果表明:有/无速度条件的引射过程均存在两个阶段,即反压影响阶段和自维持阶段,在自维持阶段,内流道存在全为超声速的截面,环境压力不会对二次流流量产生影响 当处于反压影响阶段,由于环境压力不同,不同速度条件的内流场存在差异,二次流流量也存在差别,随马赫数增加,RBCC所引射的空气流量增加 当处于自维持阶段时,不同速度条件的内流场十分相似,二次流流量也基本相同,说明二次流总温、总压相同时,马赫数对引射过程没有影响,有速度条件的引射过程可以等效为相同总温、总压的零速引射过程,这为有速度条件的二次流流量评估以及试验来流参数配置提供了便利。
- Abstract:
- In order to obtain the influence of the speed condition on the ejecting process of a RBCC(rocket based combined cycle)engine, numerical simulation was performed to investigate the ejector mode of a strut-based RBCC model at subsonic speed.The results show that the operation regimes contains two stages under the investigated speed conditions are back pressure dominating stage and self-sustaining stage.At self-sustaining stage, due to the existence of all-supersonic flow, the ambient pressure can not influence the ejecting process.When working at back pressure dominating stage, due to the different ambient pressure(the total pressure is the same), the internal flow pattern and the mass flow rate of the secondary flow are different at different Mach number while instead, the internal flow pattern and the mass flow rate of the secondary flow are almost the same at self-sustaining stage, which further shows the parameters of the secondary flow that determine the ejection process are the total pressure and temperature, irrelevant to Mach number.So, the ejection process at some speed condition can be equivalent to the ejection process at zero speed provided that their total pressure and temperature are the same, which provides the convenience for the assessment of the mass flow rate of the secondary flow at subsonic speed and the preparation for flow condition of wind tunnel test.
参考文献/References:
[1] 龚春林,陈兵.组合循环动力在水平起降天地往返飞行器上的应用[J].科技导报,2020,38(12):25-32.
[2] 张升升,郑雄,吕雅,等.国外组合循环动力技术研究进展[J].科技导报,2020,38(12):33-53.
[3] 张玫,张蒙正,刘昊.火箭基组合循环动力研究进展[J].科技导报,2020,38(12):54-68.
[4] 王亚军,何国强,秦飞,等.火箭冲压组合动力研究进展[J].宇航学报,2019,40(10):1125-1133.
[5] BULMAN M,SIEBENHAAR A.Combined cycle propulsion:Aerojet innovations for practical hypersonic vehicles[C]//17th AIAA International Space Planes and Hypersonic Systems and Technologies Conference.Reston,Virginia:AIAA,2011.
[6] 张蒙正,张玫,严俊峰,等.RBCC动力系统工作模态问题[J].火箭推进,2015,41(2):1-6.
ZHANG M Z,ZHANG M,YAN J F,et al.Discussion about work modal of RBCC power system[J].Journal of Rocket Propulsion,2015,41(2):1-6.
[7] 白菡尘,陈军.双模态冲压发动机等效热力过程与性能关系原理[M].北京:国防工业出版社,2018.
[8] SIEBENHAAR A,BONAR D,SARMONT E.The role of the strutjet engine in new global and space markets[EB/OL].https://www.semanticscholar.org/paper/The-Role-of-the-Strutjet-Engine-in-New-Global-and-Siebenhaar-Bonar/75c5 7488e9bd124296bc9a3565e0d0df69e00aca,1998.
[9] QUINN J.ISTAR:Project status and ground test engine design[C]//39th AIAA/ASME/SAE/ASEE Joint Propulsion Conference and Exhibit.Reston,Virginia:AIAA,2003.
[10] TAKEGOSHI M,TOMIOKA S,UEDA S,et al.Performances of a rocket chamber for the combined-cycle engine at various conditions[C]//14th AIAA/AHI Space Planes and Hypersonic Systems and Technologies Conference.Reston,Virginia:AIAA,2006.
[11] 黄生洪,TOHRU M,EIJIRO K.壅塞机制对 RBCC 引射模态推力增强性能的影响[C]//中国力学学会学术大会论文集.北京:中国力学学会,2005.
[12] DIJKSTRA F,MAREE A,CAPORICCI M,et al.Experimental investigation of the thrust enhancement potential of ejector rockets[C]//33rd Joint Propulsion Conference and Exhibit.Reston,Virginia:AIAA,1997.
[13] 阿勃拉莫维奇.实用气体动力学[M].梁秀彦,译.北京:高等教育出版社,1955.
[14] FABRI J,SIESTRUNCK R.Supersonic air ejectors[J].Advances in Applied Mechanics,1958,5:1-34.
[15] FABRI J,PAULON J.Theory and experiments on supersonic air-to-air ejectors[R].NACA T-M1410.
[16] 朱也夫В С,马卡伦В С.冲压和火箭冲压发动机原理[M].北京:国防工业出版社,1975.
[17] AOKI S,LEE J,MASUYA G,et al.Aerodynamic experiment on an ejector-jet[J].Journal of Propulsion and Power,2005,21(3):496-503.
[18] TANI K,KANDA T,TOKUTOME S.Aerodynamic characteristics of the combined cycle engine in an ejector jet mode[C]//43rd AIAA Aerospace Sciences Meeting and Exhibit.Reston,Virginia:AIAA,2005.
[19] 刘洋,何国强,刘佩进,等.一次火箭流量对RBCC性能影响的数值和实验研究[J].固体火箭技术,2008,31(5):439-444.
[20] 李强,刘佩进,李江,等.来流马赫数对引射火箭引射量的影响研究[J].固体火箭技术,2009,32(3):254-257.
[21] 刘晓伟,石磊,刘佩进,等.RBCC发动机引射模态进气道特性研究[J].固体火箭技术,2016,39(5):601-605.
[22] SHI L,LIU X W,HE G Q,et al.Numerical analysis of flow features and operation characteristics of RBCC inlet in ejector mode[J].Acta Astronautica,2016(127):182-196.
[23] LEHMAN M,PAL S,SANTORO R.Experimental investigation of the RBCC rocket-ejector mode[C]//36th AIAA/ASME/SAE/ASEE Joint Propulsion Conference and Exhibit.Reston,Virginia:AIAA,2000.
[24] 陈军,白菡尘.稳态引射过程自维持临界截面研究[J].推进技术,2022,43(5):74-83.
备注/Memo
收稿日期:2022-03-05 修回日期:2022-04-05
基金项目:国家重点实验室基金(STS/MY-ZY-2020-004)
作者简介:万冰(1994—),男,博士研究生,研究领域为组合循环发动机设计理论。
通信作者:白菡尘(1965—),女,博士,研究员,研究领域为吸气式发动机内流空气动力学。
更新日期/Last Update:
1900-01-01