马赫数10条件下冲压发动机内氢气燃烧特性试验

卢洪波; 林键; 金熠; 陈星; 纪锋; 吴衡毅; 刘春风; 王瑞庭; 朱浩; 杨甫江; 韦宝禧

doi:10.7638/kqdlxxb-2023.0134

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马赫数10条件下冲压发动机内氢气燃烧特性试验

研究论文 | 更新时间：2026-05-28

- 马赫数10条件下冲压发动机内氢气燃烧特性试验
- Hydrogen combustion experiments of a fullpath scramjet at a Mach 10 condition of high enthalpy shock tunnel
- 空气动力学学报 2024年42卷第4期页码：27-36
- 作者机构：
  
  1. 中国航天空气动力技术研究院,北京,100074
  2. 中国科学技术大学工程与材料科学实验中心,合肥,230026
  3. 北京动力机械研究所,北京,100074
- 作者简介：
  
  卢洪波（1985—），男，博士研究生，研究员，研究方向：冲压发动机流动/燃烧特征与试验技术. E-mail：finlhb_0605@163.com
  林键*（1984—），男，博士研究生，高级工程师，研究方向：气动热测量技术与脉冲风洞技术. E-mail：naoh52@sohu.com
- 基金信息：
  
  国家自然科学基金（U21B6003）
- DOI：10.7638/kqdlxxb-2023.0134
  中图分类号： V437;V211.751
- 纸质出版：2024
- 稿件说明：
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卢洪波, 林键, 金熠, 等. 马赫数10条件下冲压发动机内氢气燃烧特性试验[J]. 空气动力学学报, 2024, 42(4): 27−36.

LU Hongbo, LIN Jian, JIN Yi, et al. Hydrogen combustion experiments of a fullpath scramjet at a Mach 10 condition of high enthalpy shock tunnel[J]. 2024, 42(4): 27-36.
卢洪波, 林键, 金熠, 等. 马赫数10条件下冲压发动机内氢气燃烧特性试验[J]. 空气动力学学报, 2024, 42(4): 27−36. DOI： 10.7638/kqdlxxb-2023.0134

LU Hongbo, LIN Jian, JIN Yi, et al. Hydrogen combustion experiments of a fullpath scramjet at a Mach 10 condition of high enthalpy shock tunnel[J]. 2024, 42(4): 27-36. DOI： 10.7638/kqdlxxb-2023.0134.

摘要

针对高马赫数超燃冲压发动机面临的高效燃烧组织挑战，本文提出了一种凹腔后缘激波强化的高马赫数超声速燃烧组织技术，并设计了一套燃烧室采用双侧对称布置凹腔结构的三维发动机试验模型。采用OH

基化学发光光谱诊断与壁面测压相结合的试验手段，在自由活塞驱动激波风洞的名义

= 10流场中，对凹腔上游横向氢气射流的燃烧特性进行了研究，并讨论了模拟流场的重复性，给出了氢气燃烧演化特征、火焰稳定结构及释热特性。不同车次的总压等流场参数表明试验流场具有较高的重复性，可保障氢气燃烧特性的可复现性。通过观察试验过程中OH

基动态发光特征发现，在高焓激波风洞发动机试验中采用燃料提前喷注的方法使发动机流道在空气主流到来之前充盈大量的氢气，进而在主流到达发动机内的瞬间形成所谓“激波管流动-燃烧”效应，使来流空气与氢气接触面发生自点火与剧烈燃烧，产生显著不同于发动机正常工作情况下的点火与燃烧机制，但随着主流趋于平稳，“激波管流动-燃烧”效应消失，在高总温气流的自点火效应与凹腔后缘的X型激波耦合作用下，火焰稳定在凹腔上游近壁面区的氢气射流尾迹区和凹腔后缘附近的全流场中。通过分析壁面压力分布特征发现，凹腔后缘的X型激波实现了燃烧的强化与火焰的稳定，并获得了最显著的释热压升。这些结果表明高马赫数冲压发动机可利用凹腔后缘X型激波强化燃烧和稳定火焰。

Abstract

To explore how to improve the performance of scramjet engines operating at a flight Mach number around 10

we proposed a method to achieve combustion enhancement by means of the cavity-aft-shock

and designed the three-dimensional scramjet article with a both-side-symmetrically-configured cavity combustion chamber. Using a combination of the excited OH

chemiluminescenc

e visualization and wall pressure measurement

burning characteristics of the hydrogen jet injected upstream of the cavity in a highly supersonic crossflow of the scramjet combustor were experimentally studied at the nominal condition of

= 10 in a free-piston driven high enthalpy shock tunnel. The repeatability of the simulated flow field was discussed

and the evolution characteristics of hydrogen combustion

flame-stabilization structure

and heat release profiles were given. Across all experimental cases

the stagnation parameters of the freestream flow remained constant with low standard deviation

allowing for effective analysis of hydrogen combustion characteristics. The evolving features of OH

chemiluminescence indicate that the so-called "shock tube flow-combustion" in the engine article is formed at the initial stage of the crossflow establishment due to the employment of the fuel injection before the arrival of the highly supersonic crossflow

leading to the autoignition at the contact interface of the high temperature crossflow with the injected hydrogen

while the flame ultimately anchors at the jet wake of the bodyside wall and the whole flow path around the cavity aft due to the coupling interaction of the autoignition in high total temperature crossflow and cavity-aft X-type shock pattern. The OH

luminosity and wall pressure distribution features within the effective test time demonstrate that the combustion enhancement is associated with the cavity-aft X-type shock patterns

which generate the drastic heat release-induced pressure rise. The results are useful to promote combustion efficiency of high Mach number scramjet engines by means of cavity configuration presented in this paper.

关键词

Keywords

references

FERRI A . Review of scramjet propulsion technology[J ] . Journal of Aircraft, 1968 , 5 ( 1 ): 3 − 10 .

URZAY J . Supersonic combustion in air-breathing propulsion systems for hypersonic flight[J ] . Annual Review of Fluid Mechanics, 2018 , 50 ( 1 ): 593 − 627 .

李旭彦, 郑星, 薛瑞 . 超燃冲压发动机技术发展现状及相关建议[J ] . 科技中国, 2019 ( 2 ): 5 − 8 .

LING W H, HOU J L, WEI B X, et al . Technical challenge and potential solution for aerospace combined cycle engine[J ] . Journal of Propulsion Technology, 2018 , 39 ( 10 ): 2171 − 2176 (in Chinese).

Yue L J, Zhang X, Zhang Q F, et al. Research progress on high-Mach-number scramjet engine technologies[J]. Chinese Journal of Theoretical and Applied Mechanics, 2022, 54(2): 263-288 (in Chinese).

MARSHALL L, BAHM C, CORPENING G, et al. Overview with results and lessons learned of the X-43A Mach 10 flight[C]// AIAA/CIRA 13th International Space Planes and Hypersonics Systems and Technologies Conference, Capua, Italy. Reston, Virigina: AIAA, 2005.

STALKER R J, PAULL A, MEE D J, et al . Scramjets and shock tunnels—the Queensland experience[J ] . Progress in Aerospace Sciences, 2005 , 41 ( 6 ): 471 − 513 .

HIRAIWA T, ITO K, SATO S, et al . Recent progress in scramjet/combined cycle engines at JAXA, Kakuda space center[J ] . Acta Astronautica, 2008 , 63 ( 5-6 ): 565 − 574 .

SMART M . Scramjets[J ] . The Aeronautical Journal, 2007 , 111 ( 1124 ): 605 − 619 .

SURAWEERA M V, SMART M K . Shock-tunnel experiments with a Mach 12 rectangular-to-elliptical shape-transition scramjet at off-design conditions[J ] . Journal of Propulsion and Power, 2009 , 25 ( 3 ): 555 − 564 .

TURNER J C, SMART M K . Application of inlet injection to a three-dimensional scramjet at Mach 8[J ] . AIAA Journal, 2010 , 48 ( 4 ): 829 − 838 .

BARTH J E, WHEATLEY V, SMART M K . Effects of hydrogen fuel injection in a Mach 12 scramjet inlet[J ] . AIAA Journal, 2015 , 53 ( 10 ): 2907 − 2919 .

LANDSBERG W O, WHEATLEY V, SMART M K, et al . Enhanced supersonic combustion targeting combustor length reduction in a Mach 12 scramjet[J ] . AIAA Journal, 2018 , 56 ( 10 ): 3802 − 3807 .

KIRCHHARTZ R M, MEE D J, STALKER R J . Supersonic skin-friction drag with tangential wall slot fuel injection and combustion[J ] . AIAA Journal, 2012 , 50 ( 2 ): 313 − 324 .

BARTH J E, WHEATLEY V, SMART M K . Hypersonic turbulent boundary-layer fuel injection and combustion: Skin-friction reduction mechanisms[J ] . AIAA Journal, 2013 , 51 ( 9 ): 2147 − 2157 .

BARTH J E, WISE D J, WHEATLEY V, et al . Tailored fuel injection for performance enhancement in a Mach 12 scramjet e ngine[J ] . Journal of Propulsion and Power, 2019 , 35 ( 1 ): 72 − 86 .

RAZZAQI S A, SMART M K . Hypervelocity experiments on oxygen enrichment in a hydrogen-fueled scramjet[J ] . AIAA Journal, 2011 , 49 ( 7 ): 1488 − 1497 .

PETTY D J, WHEATLEY V, SMART M K, et al . Effects of oxygen enrichment on scramjet performance[J ] . AIAA Journal, 2013 , 51 ( 1 ): 226 − 235 .

CAPRA B R, BOYCE R R, KUHN M, et al . Combustion enhancement in a scramjet engine using oxygen enrichment and porous fuel injection[J ] . Journal of Fluid Mechanics, 2015 , 767 : 173 − 198 .

TAKAHASHI M, SUNAMI T, TANNO H, et al. Performance characteristics of a scramjet engine at Mach 10 to 15 flight condition[C]// AIAA/CIRA 13th International Space Planes and Hypersonics Systems and Technologies Conference, Capua, Italy. Reston, Virigina: AIAA, 2005.

TAKAHASHI M, KOMURO T, SATO K, et al. Performance characteristics of scramjet engine with different combustor shapes at hypervelocity condition over Mach 10 flight[C]// 43rd AIAA/ASME/SAE/ASEE Joint Propulsion Conference Exhibit, Cincinnati, OH. Reston, Virigina: AIAA, 2007.

SUNAMI T, ITOH K, SATOH K, et al. Mach 8 ground tests of the hypermixer scramjet for HyShot-IV flight experiment[C]// 14th AIAA/AHI Space Planes and Hypersonic Systems and Technologies Conference, Canberra, Australia. Reston, Virigina: AIAA, 2006.

TOSHIHIKO H, TEPPEI O . Shockwave effects on supersonic combustion using hypermixer struts[J ] . Physics of Fluids, 2020 , 32 ( 1 ): 16104 .

TRISTAN V. Experimental investigation of 3D thermal compression scramjet using advanced optical techniques[D]. St. Lucia, QLD, Australia: The University of Queensland, 2018.

TRISTAN V, STEFAN B, MATHEW B, et al . Thermal compression effects within a fundamental, hydrogen-fuelled scramjet[J ] . Aerospace Science and Technology, 2021 , 110 : 106499 .

ZHANG S K, LI J, HUANG Z W, et al . Combustion flow field analysis of a scramjet engine at high Mach n umber[J ] . Journal of Astronautics, 2017 , 38 ( 1 ): 80 − 88 (in Chinese).

杨甫江, 郭晟, 李亭荷. 更高马赫数超燃冲压发动机推阻力分析[C]// 中国航天第三专业信息网第三十八届技术交流会暨第二届空天动力联合会议论文集, 2017: 299-308.

HAN X, LIU Y F, ZHANG Z J, et al . The theoretical method to increase the thrust of high Mach number scramjets[J ] . Chinese Journal of Theoretical and Applied Mechanics, 2022 , 54 ( 3 ): 633 − 643 (in Chinese).

HE C, XING J W, OUYANG H, et al . Flow field and combustion characteristics analysis of scramjet under Ma 12 flight condition[J ] . Chinese Journal of Theoretical and Applied Mechanics, 2022 , 54 ( 3 ): 622 − 632 (in Chinese).

HAN Y Y, ZHANG R L, XING J W, et al . Effects of thermal nonequilibrium on cold flow in scramjets[J ] . Journal of Propulsion Technology, 2022 , 43 ( 7 ): 157 − 169 (in Chinese).

YAO X Y, WANG C, YU J, et al . High-Mach-number scramjet e ngine tests in JF12 shock tunnel[J ] . Physics of Gases, 2019 , 4 ( 5 ): 25 − 31 (in Chinese).

ZHAO R J, LIU S R, ZHOU Z, et al . Research of scramjet thrust test in shock tunnel[J ] . Journal of Experiments in Fluid Mechanics, 2022 , 36 ( 4 ): 103 − 108 (in Chinese).

WU L Y, KONG X P, LI X, et al . Experimental study on a scramjet at Mach 10 in shock tunnel[J ] . Journal of Propulsion Technology, 2021 , 42 ( 12 ): 2818 − 2825 (in Chinese).

ZHANG D Q, DENG W X, XING J W, et al . Scramjet free-jet test process at Ma 10 conditions[J ] . Journal of Aerospace Power, 2023 , 38 ( 3 ): 735 − 742 (in Chinese).

ZHANG X, ZHANG Q F, YUE L J, et al . Shock-tunnel experimental study of combustion enhancement methods for a high-Mach-number scramjet[J ] . Chinese Journal of Theoretical and Applied Mechanics, 2022 , 54 ( 5 ): 1403 − 1413 (in Chinese).

Zhou G X, Zhang X, Li J P, et al . Optical diagnostics in a detonation-driven direct-connected circular combustor fueled with hydrogen for Mach 10 scramjet[J ] . International Journal of Hydrogen Energy, 2021 , 46 ( 54 ): 27801 − 27815 .

CHEN Y F, LU H B, WEN S, et al . Thrust/Drag measurement techniques of a free flight scramjet in a shock tunnel[J ] . Acta Aerodynamica Sinica, 2022 , 40 ( 1 ): 141 − 148 (in Chinese).

LU H B, CHEN X, ZENG X Z, et al . Exploration of experimental techniques on Ma = 10 scramjets in FD-21 high enthalpy shock tunnel[J ] . Physics of Gases, 2022 , 7 ( 2 ): 1 − 12 (in Chinese).

LIN J, LU H B, WANG R T, et al . Establishing process of scramjet flow and ethylene-burning at Ma 10 conditions of FD-21 shock tunnel[J ] . Chinese Journal of Theoretical and Applied Mechanics, 2023 , 55 ( 8 ): 1788 − 1799 (in Chinese).

SHEN J M, CHEN X, BI Z X, et al . Review on expe rimental technology of high enthalpy shock tunnel[J ] . Acta Aerodynamics Sinica, 2018 , 36 ( 4 ): 543 − 554 (in Chinese).

苟光贤, 黄洁. 高焓真实气体效应试验技术研究[C]//第九届高超声速气动力(热)学术交流会议论文集, 1997.

苟光贤. 气动中心超高速所自由活塞激波风洞技术研究进展[C]// 第二届全国航空航天空气动力学前沿问题学术研讨会, 1996.

AO Y, WU K, LU H B, et al . Combustion dynamics of high Mach number scramjet under different inflow thermal nonequilibrium conditions[J ] . Acta Astronautica, 2023 , 208 : 281 − 295 .

YUAN Y M, ZHANG T C, YAO W, et al . Characterization of flame stabilization modes in an ethylene-fueled supersonic combustor using time-resolved CH* chemiluminescence[J ] . Proceedings of the Combustion Institute, 2017 , 36 ( 2 ): 2919 − 2925 .

CAI Z. Study on ignition and flame stabilization process in supersonic cavity combustor with sudden expansion of trailing edge[D]. Changsha: National University of Defense Technology, 2018 (in Chinese).

GAMBA M, MUNGAL M G . Ignition, flame structure and near-wall burning in transverse hydrogen jets in supersonic crossflow[J ] . Journal of Fluid Mechanics, 2015 , 780 : 226 − 273 .

LIU Q L, BACCARELLA D, LEE T H . Review of combustion stabilization for hypersonic airbreathing propulsion[J ] . Progress in Aerospace Sciences, 2020 , 119 : 100636 .

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