前置翼片式涡流发生器对燃烧室氢气燃料掺混特性的影响

吴龙; 王江峰; 李龙飞; 王丁

doi:10.7638/kqdlxxb-2021.0414

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前置翼片式涡流发生器对燃烧室氢气燃料掺混特性的影响

研究论文 | 更新时间：2026-05-28

- 前置翼片式涡流发生器对燃烧室氢气燃料掺混特性的影响
- Effect of front vane vortex generators on hydrogen fuel mixing characteristics in combustor
- 空气动力学学报 2023年41卷第3期页码：33-43
- 作者机构：
  
  1. 非定常空气动力学与流动控制工业和信息化部重点实验室,南京,210016
  2. 南京航空航天大学航空学院,南京,210016
- 作者简介：
  
  吴龙（1997-），男，四川简阳人，硕士研究生，研究方向：超燃冲压发动机燃烧室喷主流干扰研究. E-mail：wulong@nuaa.edu.cn
  王江峰*，教授，研究方向：高超声速空气动力学. E-mail：wangjf@nuaa.edu.cn
- 基金信息：
  
  国家数值风洞工程（NNW2019ZT7-B30，NNW2018-ZT3B08）;江苏优势学科建设工程
- DOI：10.7638/kqdlxxb-2021.0414
  中图分类号： V434+.13
- 纸质出版：2023
- 稿件说明：
移动端阅览
吴龙, 王江峰, 李龙飞, 等. 前置翼片式涡流发生器对燃烧室氢气燃料掺混特性的影响[J]. 空气动力学学报, 2023, 41(3): 33−43.

WU Long, WANG Jiangfeng, LI Longfei, et al. Effect of front vane vortex generators on hydrogen fuel mixing characteristics in combustor[J]. 2023, 41(3): 33-43.
吴龙, 王江峰, 李龙飞, 等. 前置翼片式涡流发生器对燃烧室氢气燃料掺混特性的影响[J]. 空气动力学学报, 2023, 41(3): 33−43. DOI： 10.7638/kqdlxxb-2021.0414

WU Long, WANG Jiangfeng, LI Longfei, et al. Effect of front vane vortex generators on hydrogen fuel mixing characteristics in combustor[J]. 2023, 41(3): 33-43. DOI： 10.7638/kqdlxxb-2021.0414.

摘要

超声速来流与燃料的充分掺混是超声速燃烧的关键技术，直接关系到吸气式高超声速推进系统的总体性能。本文通过在射流口前安装翼片式涡流发生器以促进燃料与空气的掺混。基于SST

$k{\text{-}}\omega$

img text_id='M1' class='formula-img' style='display:none;' src='2021-414_M1.jpg'>

湍流模型的RANS方法，对带有翼片式涡流发生器的超燃冲压发动机燃烧室模型内氢气横向喷流冷流流场进行了数值模拟，对比分析涡流发生器高度和长度不同的条件下燃烧室内的流场结构、涡流强度、氢气与空气掺混特性、燃烧室总压损失的规律。结果表明，翼片式涡流发生器能够提高涡流强度并大幅提高燃烧室内的掺混性能。随着涡流发生器高度和长度的增加，流场结构间的干扰增强，导致涡流强度和穿透深度增加，从而提升掺混效率。与不安装涡流发生器情况相比，涡流发生器能提升氢燃料的穿透深度超过170%，减少燃料掺混距离70%以上。更加复杂的流场结构同时会增大燃烧室的总压损失，并随着涡流发生器高度和长度的增加而增大。相较于掺混性能的提升，总压损失的增大幅度相对小很多，说明通过合理的参数选择，翼片式涡流发生器能够有效提升燃烧室的掺混性能。

Abstract

The mixing process plays an important role in supersonic combustion

and sufficient mixing between the incoming supersonic air and the fuel is closely related to the overall performance of the airbreathing hypersonic propulsion system. In the present study

vane vortex generators are placed in front of the injector to promote the mixing of the fuel and the a

ir. The three-dimensional compressible N-S equations and the two-equation SST

turbulence model are used to simulate the cold flow field of the hydrogen transverse jet in a scramjet combustor. Effects of the vane vortex generator height and length on the flow field structure

vorticity intensity

mixing characteristics of hydrogen/air and total pressure loss in the combustor have been investigated. The results show that the vane vortex generator can greatly improve the vorticity intensity and the mixing performance of the combustor. With the increase of the vortex generator height and length

the interaction among flow field structures increases

resulting in the increase of the vorticity intensity and penetration depth

thus improves the fuel mixing efficiency in the combustor. Compared to the scheme without vortex generators

the penetration depth of the hydrogen jet can be increased by more than 170%

and the distance of the complete mixing can be reduced by more than 70%. More complex flow field structures also increase the total pressure loss of the combustor

and this effect increases with the height and length of the vortex generator. Compared to the improvement of the mixing performance

the increase of the total pressure loss is much smaller

indicating that the vane vortex generator can effectively improve the mixing performance of the combustor through reasonable parameter selection.

关键词

Keywords

references

CHOUBEY G, YUVARAJAN D, HUANG W, et al. Recent research progress on transverse injection technique for scramjet applications-a brief review[J]. International Journal of Hydrogen Energy, 2020, 45(51): 27806-27827. DOI:10.1016/j.ijhydene.2020.07.098

SHARMA V, ESWARAN V, CHAKRABORTY D. Determination of optimal spacing between transverse jets in a SCRAMJET engine[J]. Aerospace Science and Technology, 2020, 96: 105520. DOI:10.1016/j.ast.2019.105520

HUANG W. Transverse jet in supersonic crossflows[J]. Aerospace Science and Technology, 2016, 50: 183-195. DOI:10.1016/j.ast.2016.01.001

ZHAO M J, YE T H, CAO C M, et al. Study of sonic injection from circular injector into a supersonic cross-flow using large eddy simulation[J]. International Journal of Hydrogen Energy, 2016, 41(39): 17657-17669. DOI:10.1016/j.ijhydene.2016.07.018

SCHETZ J A, MADDALENA L, BURGER S K. Molecular weight and shock-wave effects on transverse injection in supersonic flow[J]. Journal of Propulsion and Power, 2010, 26(5): 1102-1113. DOI:10.2514/1.49355

HUANG W, LIU J, JIN L, et al. Molecular weight and injector configuration effects on the transverse injection flow field properties in supersonic flows[J]. Aerospace Science and Technology, 2014, 32(1): 94-102. DOI:10.1016/j.ast.2013.12.006

ASO S, INOUE K, YAMAGUCHI K, et al. A study on supersonic mixing by circular nozzle with various injection angles for air breathing engine[J]. Acta Astronautica, 2009, 65(5-6): 687-695. DOI:10.1016/j.actaastro.2009.01.051

WU H, WANG J H, HUANG W, et al. Research progress on shock wave/boundary layer interactions and flow controls induced by micro vortex generators[J]. Acta Aeronautica et Astronautica Sinica, 2021, 42(6): 25371. (in Chinese)

ZHANG Y, TAN H J, WANG Z Y, et al. Progress of shock wave/boundary layer interaction and its control in inlet[J]. Journal of Propulsion Technology, 2020, 41(2): 241-259. (in Chinese)

LI L Q, HUANG W, YAN L. Mixing augmentation induced by a vortex generator located upstream of the transverse gaseous jet in supersonic flows[J]. Aerospace Science and Technology, 2017, 68: 77-89. DOI:10.1016/j.ast.2017.05.016

ZHANG Y J, LIU W D, WANG B, et al. Effects of micro-ramp on transverse jet in supersonic crossflow[J]. Acta Astronautica, 2016, 127: 160-170. DOI:10.1016/j.actaastro.2016.05.032

LI L Q, HUANG W, FANG M, et al. Investigation on three mixing enhancement strategies in transverse gaseous injection flow fields: a numerical study[J]. International Journal of Heat and Mass Transfer, 2019, 132: 484-497. DOI:10.1016/j.ijheatmasstransfer.2018.12.038

DONG X R, CHEN Y H, DONG G, et al. Study on wake structure characteristics of a slotted micro-ramp with large-eddy simulation[J]. Fluid Dynamics Research, 2017, 49(3): 035507. DOI:10.1088/1873-7005/aa658d

LIU C Y. Study on mixing, ignition and combustion stabilization mechanism of wall-injection fuel jet in supersonic flows[D]. Changsha: National University of Defense Technology, 2019 (in Chinese).

HUANG W, TAN J G, LIU J, et al. Mixing augmentation induced by the interaction between the oblique shock wave and a sonic hydrogen jet in supersonic flows[J]. Acta Astronautica, 2015, 117: 142-152. DOI:10.1016/j.actaastro.2015.08.004

SCHLATTER P, ÖRLÜ R. Assessment of direct numerical simulation data of turbulent boundary layers[J]. Journal of Fluid Mechanics, 2010, 659: 116-126. DOI:10.1017/s0022112010003113

LIANG C H, SUN M B, LIU Y, et al. Numerical study of flow structures and mixing characteristics of a sonic jet in supersonic crossflow[J]. Acta Astronautica, 2020, 166: 78-88. DOI:10.1016/j.actaastro.2019.10.008

WANG Y H. Numerical study on supersonic combustion flow with unsteady jet[D]. Nanjing: Nanjing University of Aeronautics and Astronautics, 2019 (in Chinese).

PUDSEY A S, BOYCE R R, WHEATLEY V. Hypersonic viscous drag reduction via multi-porthole injector arrays[J]. Journal of Propulsion and Power, 2013, 29(5): 1087-1096. DOI:10.2514/1.b34782

SUN M B, HU Z W. Mixing in nearwall regions downstream of a sonic jet in a supersonic crossflow at Mach 2.7[J]. Physics of Fluids, 2018, 30(10): 106102. DOI:10.1063/1.5045752

HUANG W, DU Z B, YAN L, et al. Supersonic mixing in airbreathing propulsion systems for hypersonic flights[J]. Progress in Aerospace Sciences, 2019, 109: 100545. DOI:10.1016/j.paerosci.2019.05.005

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