流体力学与飞行力学

吸气式连续旋转爆震与来流相互作用

  • 王超 ,
  • 刘卫东 ,
  • 刘世杰 ,
  • 蒋露欣 ,
  • 苏义
展开
  • 1. 国防科学技术大学 高超声速冲压发动机技术重点试验室, 长沙 410073;
    2. 陆军装备部武汉军代局驻常德军代室, 常德 415000
王超,男,博士研究生。主要研究方向:高超声速推进技术。Tel:0731-84574758 E-mail:emspire529@163.com;刘卫东,男,博士,教授,博士生导师。主要研究方向:高超声速推进技术。Tel:0731-84574758 E-mail:WDLiu@nudt.edu.cn

收稿日期: 2015-04-28

  修回日期: 2015-07-27

  网络出版日期: 2015-08-18

基金资助

国家自然科学基金(51306202,51476186,91441201)

Interaction of air-breathing continuous rotating detonation with inflow

  • WANG Chao ,
  • LIU Weidong ,
  • LIU Shijie ,
  • JIANG Luxin ,
  • SU Yi
Expand
  • 1. Science and Technology on Scramjet Laboratory, National University of Defense Technology, Changsha 410073, China;
    2. The Office of Wuhan Military Representative Bureau Army Equipment Department in Changde, Changde 415000, China

Received date: 2015-04-28

  Revised date: 2015-07-27

  Online published: 2015-08-18

Supported by

National Natural Science Foundation of China (51306202, 51476186, 91441201)

摘要

以加热空气为氧化剂,氢气为燃料,开展了吸气式连续旋转爆震试验,研究了连续旋转爆震与来流的相互作用。通过测量隔离段和爆震燃烧室压力,发现了3种相互作用类型:类型1:连续旋转爆震对空气来流不产生影响;类型2:空气来流中存在高频压力振荡,且主频与连续旋转爆震波的传播频率相同,但来流总压不变;类型3:空气来流中存在与连续旋转爆震波传播频率相同的高频压力振荡,且来流总压升高。初步对比了爆震燃烧室尺寸的影响,结果表明随着爆震燃烧室面积的减小,连续旋转爆震对来流的影响增强,影响区域也向上游扩展。

本文引用格式

王超 , 刘卫东 , 刘世杰 , 蒋露欣 , 苏义 . 吸气式连续旋转爆震与来流相互作用[J]. 航空学报, 2016 , 37(5) : 1411 -1418 . DOI: 10.7527/S1000-6893.2015.0210

Abstract

Experiments on continuous rotating detonation (CRD) in the air-breathing mode were performed, and vitiated air and hydrogen were used as oxidizer and fuel, respectively. The pressures in the isolator and detonation combustor are acquired, and three types of interactions of the CRD with the air flow are found. In Type 1, the air flow in the isolator is not affected by the CRD, and neither high-frequency pressure oscillation in the isolator, nor total pressure rise of the air flow is excited. In Type 2, the CRD leads to high-frequency oscillation in the isolator and its dominant frequency is the same as the CRD; the total pressure of the air flow remains constant. In Type 3, the pressure in the isolator oscillates with the same high-frequency of the CRD and the total pressure of the air flow is increased. The influence of the detonation combustor size is preliminarily investigated and results show that the CRD strengthens as the detonation combustor size decreases, and the influence of the CRD propagates towards upstream.

参考文献

[1] WOLANSKI P. Detonative propulsion[J]. Proceedings of the Combustion Institute, 2013, 34(1):125-158.
[2] LU F K, BRAUN E M. Rotating detonation wave propulsion:Experimental challenges, modeling, and engine concepts[J]. Journal of Propulsion and Power, 2014, 30(5):1125-1142.
[3] KAILASANATH K. Review of propulsion applications of detonation waves[J]. AIAA Journal, 2000, 38(9):1698-1708.
[4] LIU S J, LIN Z Y, SUN M B, et al. Thrust vectoring of a continuous rotating detonation engine by changing the local injection pressure[J]. Chinese Physics Letters, 2011, 28(9):094704.
[5] DANIAU E, FALEMPIN F, ZHDAN S. Pulsed and rotating detonation propulsion systems:First step toward operational engines:AIAA-2005-3233[R]. Reston:AIAA,2005.
[6] BYKOVSKII F A, ZHDAN S A, VEDERNIKOV E F. Continuous spin detonations[J]. Journal of Propulsion and Power, 2006, 22(6):1204-1216.
[7] BRAUN E M, LU F K, WILSON D R, et al. Airbreathing rotating detonation wave engine cycle analysis[J]. Aerospace Science and Technology, 2012, 27:201-208.
[8] 刘世杰, 王超, 蒋露欣, 等. 连续旋转爆震冲压发动机直连式试验[C]//第十六届全国激波与激波管学术会议. 北京:中国力学学会, 2014. LIU S J, WANG C, JIANG L X, et al. Experimental research on the continuous rotating detonation ramjet engine[C]//Proceeding of the 16th National Symposium on Shock Waves. Beijing:Chinese Society of Theoretical and Applied Mechanics, 2014(in Chinese).
[9] 王超, 刘卫东, 刘世杰, 等. 高总温来流下的连续旋转爆震验证试验[J]. 推进技术, 2016, 37(3):578-584. WANG C, LIU W D, LIU S J, et al. Validating experiment of continuous rotating detonation under high total temperature air[J]. Journal of Propulsion Technology, 2016, 37(3):578-584(in Chinese).
[10] 蒋露欣. 吸气式连续旋转爆震发动机工作特性研究[D]. 长沙:国防科学技术大学, 2014. JIANG L X. Investigations on working characteristics of air-breathing continuous rotating detonation engine[D] Changsha:National University of Defense Technology, 2014(in Chinese).
[11] WANG C, LIU W D, LIU S J, et al. Experimental investigation on detonation combustion patterns of hydrogen/vitiated air within annular combustor[J]. Experimental Thermal and Fluid Science, 2015, 66:269-278.
[12] BYKOVSKII F A, VEDERNIKOV E F. Continuous detonation of a subsonic flow of a propellant[J]. Combustion, Explosion, and Shock Waves, 2003, 39(3):323-334.
[13] ZHDAN S A, RYBNIKOV A I. Numerical modeling of continuous detonation in a combustor with a plane diffuser with a supersonic flow velocity:ICDERS 2013-0055[R]. Taipei:ICDERS, 2013.
[14] SCHWER D A, KAILASANATH K. Feedback into mixture plenums in rotating detonation engines:AIAA-2012-0617[R]. Reston:AIAA, 2012.
[15] SCHWER D A, KAILASANATH K. On reducing feedback pressure in rotating detonation engines:AIAA-2013-1178[R]. Reston:AIAA, 2013.
[16] BRAUN E M, BALCAZAR T S, WILSON D R, et al. Experimental study of a high-frequency fluidic valve fuel injector[J]. Journal of Propulsion and Power, 2012, 28(5):1121-1125.
[17] FOTIA M L, HOKE J L, SCHAUER F. Propellant plenum dynamics in a two-dimensional rotating detonation experiment:AIAA-2014-1013[R]. Reston:AIAA, 2014.
[18] ANDRUS I Q, KING P I, FOTIA M, et al. Experimental analogue of a pre-mixed rotating detonation engine in plane flow:AIAA-2015-1105[R]. Reston:AIAA, 2015.
[19] LIU S J, LIN Z Y, LIU W D, et al. Experimental realization of H2/Air continuous rotating detonation in a cylindrical combustor[J]. Combustion Science and Technology, 2012, 184(9):1302-1317.
[20] DEBARMORE N D, KING P I, SCHAUER F R, et al. Nozzle guide vane integration into rotating detonation engine:AIAA-2013-1030[R]. Reston:AIAA, 2013.
[21] KINDRACKI J, KOBIERA A, WOLANSKI P, et al. Experimental and numerical study of the rotating detonation engine in Hydrogen-Air mixtures[J]. Progress in Propulsion Physics, 2011, 2:555-582.
[22] SUCHOCKI J A, YU S-T J, HOKE J L, et al. Rotating detonation engine operation:AIAA-2012-0119[R]. Reston:AIAA, 2012.
[23] LIU S J, LIN Z Y, LIU W D, et al. Experimental and three-dimensional numerical investigations on H2/air continuous rotating detonation wave[J]. Journal of Aerospace Engineering, 2013, 227(2):326-341.

文章导航

/