限流方法解耦燃烧与喷射过程的合理性研究

推进技术 ›› 2017, Vol. 38 ›› Issue (3): 611-619.

限流方法解耦燃烧与喷射过程的合理性研究

王宇航^1,2,宋文艳^1,2,白菡尘²,陈亮^1,2

西北工业大学动力与能源学院，陕西西安 710072; 中国空气动力研究与发展中心超高速空气动力研究所高超声速冲压发动机技术重点实验室，四川绵阳 621000,西北工业大学动力与能源学院，陕西西安 710072; 中国空气动力研究与发展中心超高速空气动力研究所高超声速冲压发动机技术重点实验室，四川绵阳 621000,中国空气动力研究与发展中心超高速空气动力研究所高超声速冲压发动机技术重点实验室，四川绵阳 621000,西北工业大学动力与能源学院，陕西西安 710072; 中国空气动力研究与发展中心超高速空气动力研究所高超声速冲压发动机技术重点实验室，四川绵阳 621000

发布日期:2021-08-15
作者简介:王宇航，男，博士生，研究领域为航空宇航推进理论与工程。
基金资助:
高超声速冲压发动机技术重点实验室开放课题(STSKFKT2012002)。

Rationality Study of Flow Chock for Decoupling Combustion and Injection Process

School of Power and Energy，Northwestern Polytechnical University，Xi’an 710072，China; Science and Technology on Scramjet Laboratory，Hypervelocity Aerodynamics Institute of CARDC， Mianyang 621000，China,School of Power and Energy，Northwestern Polytechnical University，Xi’an 710072，China; Science and Technology on Scramjet Laboratory，Hypervelocity Aerodynamics Institute of CARDC， Mianyang 621000，China,Science and Technology on Scramjet Laboratory，Hypervelocity Aerodynamics Institute of CARDC， Mianyang 621000，China and School of Power and Energy，Northwestern Polytechnical University，Xi’an 710072，China; Science and Technology on Scramjet Laboratory，Hypervelocity Aerodynamics Institute of CARDC， Mianyang 621000，China

Published:2021-08-15

摘要/Abstract

摘要： 为了研究双模态超燃冲压发动机燃烧室在燃烧诱导的高背压环境下燃料的输运和分布情况，采用了限流方法模拟燃烧诱导的高背压环境。针对燃烧室中凹槽上游氢气燃料喷射工况的研究发现，限流试验的压力分布与燃烧试验压力分布在燃烧室前半段比较接近，证明二者的流场在燃料喷射段有一定的相似程度；数值模拟结果表明，相较于低背压状态下62%的混合效率，高背压状态下混合效率提高到了87%，并且燃烧状态下拍摄的火焰区域与限流状态下数值模拟的燃料的可燃质量分数范围相符，证明了限流方法解耦燃烧与喷射过程的合理性。

关键词: 超燃冲压发动机；限流；燃烧工况模拟；燃料射流发展；实验与数值分析

Abstract: In order to investigate fuel transportation and distribution in high backpressure dual-mode scramjet combustor environment，mechanical blockage methods was used to simulate high backpressure induced by combustion condition. It is found that in the upstream part of the combustor the pressure distribution in chocking case is consistent with combustion case when hydrogen fuel is injected upstream of cavity，this proved that the flow field in both cases have a certain degree of similarity. Numerical simulation results indicate that mixing efficiency increased to 87% in high backpressure condition，while that in low backpressure condition is 62%. In addition，the flame zone in combustion case which was shot by camera is consistent with combustible mass fraction contour line obtained by numerical simulation，this proved the rationality of flow chocking for decouple combustion environment and injection process.

Key words: Scramjet；Flow chocking；Combustion case simulation；Fuel injection process；Experiment and numerical simulation

王宇航,宋文艳,白菡尘,陈亮. 限流方法解耦燃烧与喷射过程的合理性研究[J]. 推进技术, 2017, 38(3): 611-619.

WANG Yu-hang^1,2,SONG Wen-yan^1,2,BAI Han-chen²,CHEN Liang^1,2. Rationality Study of Flow Chock for Decoupling Combustion and Injection Process[J]. Journal of Propulsion Technology, 2017, 38(3): 611-619.

参考文献

[1] Rogers R C. A Study of the Mixing of Hydrogen Injected Normal to a Supersonic Airstream[R]. NASA TN D-6114, 1971.
[2] Rogers R C. Mixing of Hydrogen Injected from Multiple Injectors Normal to a Supersonic Airstream[R]. NASA TN D-6476, 1971.
[3] Orth R C, Schetx J A, Billig F S. The Interaction and Penetration of Gaseous Jets in Supersonic Flow[R]. NASA CR-1368, 1967.
[4] Northam G B, Anderson G Y. Survey of Supersonic Combustion Ramjet Research at Langley[R]. AIAA 86-37079.
[5] Ebrahimi H B, Malo-Molina F J, Gaitonde D V. Numerical Simulation of Injection Strategies In a Cavity-Based Supersonic Combustor [J]. Journal of Propulsion and Power, 2012, 28(5): 991-999.
[6] Gruber M R, Donbar J M, Carter C D. Mixing and Combustion Studies Using Cavity-Based Flameholders in a Supersonic Flow[J]. Journal of Propulsion and Power, 2004, 20, (5): 769-778.
[7] Hsu K Y, Carter C, Crafton J, et al. Fuel Distribution About a Cavity Flameholder in Supersonic Flow[R]. AIAA 2000-3585.
[8] Yamauchi H, Choi B, Takae K, et al. Flowfield Characteristics of a Transverse Jet into Supersonic Flow with Pseudo-Shock Wave[J]. Shock Waves, 2012(22): 533-545.
[9] Micka D J, Driscoll J F. Combustion Characteristics of a Dual-Mode Scramjet Combustor with Cavity Flame Holder[J]. Proceedings of the Combustion Institute, 2009(32): 2397-2404.
[10] Fotia M L, Driscol J F. Ram-Scram Transition and Flame/Shock-Train Interactions in a Model Scramjet Experiment [J]. Journal of Propulsion and Power, 2013, 29, (1): 261-273.
[11] Tatman B J, Rockwell R D, Goyne C P, et al. Experimental Study of Vitiation Effects on Flameholding in a Cavity Flameholder[J]. Journal of Propulsion and Power, 2013, 29, (2): 417-423.
[12] Donohue J M. Dual-Mode Scramjet Flameholding Operability Measurements[J]. Journal of Propulsion and Power, 2014, 30, (3): 592-603.
[13] 田野, 乐嘉陵, 杨顺华, 等. 空气节流对超燃燃烧室流场结构与燃料混合影响的数值研究[J]. 推进技术, 2013, 34(1): 54-61. (TIAN Ye, LE Jia-ling, YANG Shun-hua, et al. Numerical Study on Air Throttling Influence of Flow Structure and Fuel-Air Mixing in Scramjet Combustor[J]. Journal of Propulsion Technology, 2013, 34(1): 54-61.)
[14] 郭帅帆, 宋文艳, 李建平, 等. 燃烧加热污染空气对超燃冲压发动机性能影响研究[J]. 推进技术, 2013, 34(4): 493-498. (GUO Shuai-fan, SONG Wen-yan, LI Jian-ping, et al. Numerical Investigation of Effects of Vitiation Air on Scramjet Performance[J]. Journal of Propulsion Technology, 2013, 34(4): 493-498.)
[15] Settles G S, Baca B K, Williams D R, et al. A Study of Reattachment of a Free Shear Layer in Compressible Turbulent Flow[R]. AIAA 80-1408.
[16] McDaniel J C, Fletcher D G, Hartfield R J, et al. Transverse Injection into Mach 2 Flow behind a Rearward-Facing Step-A 3-D, Compressible Flow Test Case for Hypersonic Combustor CFD Validation[R]. AIAA 92-31693.
[17] Heisie W H, Pratt D T. Hypersonic Airbreathing Propulsion[M]. Washington: AIAA Education Series, 1993.　　　　　　　　　　　　　　收稿日期:2015-10-13；修订日期:2015-12-03。基金项目:高超声速冲压发动机技术重点实验室开放课题(STSKFKT2012002)。作者简介:王宇航,男,博士生,研究领域为航空宇航推进理论与工程。E-mail: wyh19910905@sina.com(编辑:朱立影)