航天推进技术研究院主办
[1]杜 泉,付秀文.火箭冲压组合发动机部件缩尺关系理论初探[J].火箭推进,2018,44(02):18-22.
DU Quan,FU Xiuwen.Theoretical analysis on scaling relation of components for rocket ramjet combined engine[J].Journal of Rocket Propulsion,2018,44(02):18-22.
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DU Quan,FU Xiuwen.Theoretical analysis on scaling relation of components for rocket ramjet combined engine[J].Journal of Rocket Propulsion,2018,44(02):18-22.
火箭冲压组合发动机部件缩尺关系理论初探
《火箭推进》[ISSN:1672-9374/CN:CN 61-1436/V]
卷:
44
期数:
2018年02期
页码:
18-22
栏目:
研究与设计
出版日期:
2018-04-30
- Title:
- Theoretical analysis on scaling relation of components for rocket ramjet combined engine
- 文章编号:
- 1672-9374(2018)02-0018-05
- 分类号:
- V430-34
- 文献标志码:
- A
- 摘要:
- 为了使小尺度火箭冲压组合发动机的试验结果支撑中大尺度发动机的研制,从火箭冲压组合发动机各个部件的工作原理出发,理论分析了火箭冲压组合发动机部件缩尺关系,构建了小尺度发动机部件与中大尺度发动机部件之间的缩尺关系。研究表明:液态碳氢燃料火箭冲压组合发动机缩尺关系区别于氢燃料超燃冲压发动机的“压力-长度”缩尺关系; 发动机各部件的缩尺关系差异明显; 进排气系统可采用几何缩尺关系; 隔离段、燃料喷注器、火焰稳定装置遵循不同的缩尺关系; 燃料穿透深度与发动机尺寸呈线性关系,而蒸发和雾化与发动机尺度无关; 火箭推力室缩尺可按照缩尺因子改变火箭推力室的数量实现。
- Abstract:
- Based on the operating principle of each component for rocket ramjet combined engine, the scaling relation of components for rocket ramjet combined engine was theoretically analyzed, and the scaling relation between the components of small size engine and midsize engine or large size engine was established to make the test results of small size rocket ramjet combined engine support the development of large size engine. The analysis results show that the scaling relation of the hydrocarbon fueled rocket ramiet combined engine is different from the pressure-length scaling relation of hydrogen fueled scramjet engine; the scaling relation of all the components for the two kinds of engines is obviously different; geometric scaling relation can be adopted for the intake and exhaust system; the scaling of isolator, fuel injectors and flame stabilizing device abides by different scaling relation; the penetration depth of liquid fuel is linear relation with engine size, but the atomization and evaporation of liquid fuel has no relation with engine size; the scaling of thrust chamber can be realized by changing the number of thrust chambers according to the scale factor.
参考文献/References:
[1] MUTZMAN R, MURPHY J, HANK J. The X-51A scramjet engine flight demonstration program: AIAA 2008-2540 [R]. Reston: AIAA, 2008.
[2] 李文杰,牛文,叶蕾.美国准备地面试验10倍于X-51A 的超燃冲压发动机[J].飞航导弹,2015(3):10-13.
[3] PULSONETTI M V, STALKER R. A study of scramjet scaling: AIAA 96-4533 [R]. Reston: AIAA, 1996.
[4] CURRAN E T, MURTHY S N B. Scramjet propulsion: AIAA education series [R]. USA: AIAA, 2000.
[5] SEGALCorin. The scramjet engine processes and characteristics [M]. UK: Cambridge University Press, 2009.
[6] 张红军,沈清.新型高超声速进气道边界层人工转捩方法研究[J].实验流体力学,2016,30(2):75-78.
[7] 周正,贺旭照,卫锋,等. 密切曲内锥乘波前体进气道低马赫数性能试验研究[J].推进技术, 2016,37(8):1455-1460.
[8] 高文智,李祝飞,杨基明.一种鼻锥钝化高超声速轴对称进气道流动特性实验,航空学报[J],2015,36(1):302-310.
[9] 杜声同,严传俊.航空燃气轮机燃烧与燃烧室[M].西安:西北工业大学出版社,1994.
[10] LIN K C, KENNEDY P J, JACKSON T A. Penetration heights of liquid jets in high-speed crossflows: AIAA 2002-0873 [R]. Reston, USA: AIAA, 2002.
[11] 严传俊,范玮.燃烧学[M].西安:西北工业大学出版社,2005.
[12] CHUNG K L. Combustion physics [M]. UK: Cambridge University Press, 2006.
[13] DRISCOLL J F, RASMUSSEN C C. Correlation and analysis of blowout limits of flames in high-speed airflows [J]. Journal of propulsion and power, 2005, 21(6): 111-119.
[14] SCHEFER R W, NAMAZIAN M, KELLY J, et al. Effect of confinement on bluff-body burner recirculation zone characteristics and flame stability [J]. Combustion science and technology, 1996, 120(1): 185-211.
[15] 张贵田.高压补燃液氧煤油发动机[M].北京:国防工业出版社,2005.
[16]马列波,丰松江,冯伟,等.隔板喷嘴排列方式对推力室燃烧流场影响研究[J].火箭推进,2016,42(3):26-32.
MA Liebo,FENG Songjiang,FENG Wei, et al. Influence of baffle injection distribution on combustion fluid field in thrust chamber[J].Journal of rocket propulsion,2016,42(3):26-32.
备注/Memo
收稿日期:2016-11-20
基金项目: 国家863项目(2014AA7023026)
作者简介: 杜泉(1981—),男,高级工程师,研究领域为组合动力技术
更新日期/Last Update:
1900-01-01