连续旋转爆轰发动机冷流场的混合特性研究

doi:10.7527/S1000-6893.2016.0108

流体力学与飞行力学

本期目录 | 过刊浏览 | 高级检索

前一篇 | 后一篇

连续旋转爆轰发动机冷流场的混合特性研究

周蕊¹, 李晓鹏²

1. 北京应用物理与计算数学研究所计算物理重点实验室, 北京 100094;
2. 中国科学院力学研究所高温气体动力学国家重点实验室, 北京 100190

收稿日期:2016-01-11 修回日期:2016-03-31 出版日期:2016-12-15 发布日期:2016-04-08
通讯作者: 周蕊,Tel.:010-59872153,E-mail:ameliazhr@163.com E-mail:ameliazhr@163.com
作者简介:周蕊,女,博士,助理研究员。主要研究方向:爆轰数值模拟。Tel.:010-59872153,E-mail:ameliazhr@163.com
基金资助:
国家自然科学基金（11602028，11502029）

Numerical investigation of mixing characteristic of cold continuously rotating detonation engine

ZHOU Rui¹, LI Xiaopeng²

1. Key Laboratory of Computational Physics, Institute of Applied Physics and Computational Mathematics, Beijing 100094, China;
2. State Key Laboratory of High Temperature Gas Dynamics, Institute of Mechanics, Chinese Academy of Sciences, Beijing 100190, China

Received:2016-01-11 Revised:2016-03-31 Online:2016-12-15 Published:2016-04-08
Supported by:
National Natural Science Foundation of China (11602028, 11502029)

摘要/Abstract

摘要：

连续旋转爆轰发动机（CRDE）中燃料和氧化剂的快速掺混是实现爆轰波成功起爆和稳定传播的重要前提，然而目前国际上关于这方面的研究还相对较少。本文采用大涡模拟（LES）方法，对非预混CRDE中燃料和氧化剂的混合过程及其主要机理开展深入研究。研究结果表明，非预混CRDE流场中存在欠膨胀特征、大尺度涡结构，以及回流区等复杂的流动现象，其中由于Kelvin-Helmholtz（K-H）不稳定性产生的大尺度湍流涡结构是促进氢/氧混合的主要机制。此外，本文还考察了氧气喷注位置对非预混CRDE的流场结构和混合特征的影响，发现氧气喷注位置会影响射流剪切层形态、涡尺度，以及回流区分布等，进而影响氢气和氧气射流的混合过程和混合程度。与其他进气位置相比，氧气在靠近内壁面喷注时更有利于氢/氧的快速掺混。

关键词: 连续旋转爆轰发动机, 非预混喷注, 大涡模拟, 混合, 喷注位置, 爆轰

Abstract:

Rapid mixing of fuel and oxidizer is the necessary condition for successful initiation and stable propagation of detonation in continuously rotating detonation engine (CRDE). However, there has been few studies on the mixing characteristic of fuel/oxidizer. Two-dimensional larger eddy simulation (LES) is carried out to investigate the hydrogen/oxygen injection and mixing processes in non-premixed CRDE, and reveal the fuel/oxidizer mixing process and main mechanism. Results show that there are underexpanded feature, large scale eddy structure and recirculation zone in the non-premixed CRDE. The turbulence eddy structure generated by the Kelvin-Helmholtz (K-H) instability is the main mechanism for promoting the hydrogen/oxygen mixing. The influence of injection position of oxygen jet on the flow structure and mixing characteristics is also explored. It is found that the injection position of oxygen jet can affects the jet shear layer, vortex size and recirculation zone distribution, and then the mixing process and the mixing degree of the hydrogen and oxygen jets. It is more conducive to rapid mixing of hydrogen/oxygen when the oxygen is injected near the inner wall rather than at other injection positions of CRDE.

Key words: continuously rotating detonation engine, non-premixed injection, large eddy simulation, mixing, injection position, detonation

中图分类号:

V231.2⁺2

周蕊, 李晓鹏. 连续旋转爆轰发动机冷流场的混合特性研究[J]. 航空学报, 2016, 37(12): 3668-3674.

ZHOU Rui, LI Xiaopeng. Numerical investigation of mixing characteristic of cold continuously rotating detonation engine[J]. ACTA AERONAUTICAET ASTRONAUTICA SINICA, 2016, 37(12): 3668-3674.

参考文献

[1] WOLANSKI P. Detonation propulsion[J]. Proceedings of the Combustion Institute, 2013, 34:125-158.
[2] FAN W, YAN C J, HUANG X Q, et al. Experimental investigation on two-phase pulse detonation engine[J]. Combustion and Flame, 2003, 133(4):441-450.
[3] 张义宁, 唐豪, 王家骅, 等. 预爆管式脉冲爆震原型机试验研究[J]. 航空学报, 2009, 30(3):391-396. ZHANG Y N, TANG H, WANG J H, et al. Experimental investigation on PDE prototype with initiator[J]. Acta Aeronautica et Astronautica Sinica, 2009, 30(3):391-396(in Chinese).
[4] VOITSEKHOVSKII B V. Stationary spin detonation[J]. Soviet Journal of Applied Mechanics and Technical Physics, 1960(3):157-164.
[5] BYKOVSKII F A, ZHDAN S A, EVGENII F V. Continuous spin detonations[J]. Journal of Propulsion and Power, 2006, 22(6):1204-1216.
[6] KINDRACKI J, WOLANSKI P, GUT Z. Experimental research on the rotating detonation in gaseous fuels-oxygen mixtures[J]. Shock Waves, 2011, 21(2):75-84.
[7] ZHOU R, WU D, LIU Y, et al. Particle path tracking method in two- and three-dimensional continuously rotating detonation engines[J]. Chinese Physics B, 2014, 23(12):1-9.
[8] LIU Y S, WANG Y H, LI Y S, et al. Spectral analysis and self-adjusting mechanism for oscillation phenomenon in hydrogen-oxygen continuously rotating detonation engine[J]. Chinese Journal of Aeronautics, 2015, 28(3):669-675.
[9] LIU S J, LIN Z Y, LIU W D. Experimental and three-dimensional numerical investigations on H₂/air continuous rotating detonation wave[J]. Proc IMechE Part G:Journal of Aerospace Engineering, 2013, 227(2):326-341.
[10] PENG L, WANG D, WU X S, et al. Ignition experiment with automotive spark on rotating detonation engine[J]. International Journal of Hydrogen Energy, 2015, 40(26):8465-8474.
[11] 邵业涛, 刘勐, 王健平. 圆柱坐标系下连续旋转爆轰发动机的数值模拟[J]. 推进技术, 2009, 30(6):717-721. SHAO Y T, LIU M, WANG J P. Numerical simulation of continuous rotating detonation engine in column coordinate[J]. Journal of Propulsion Technology, 2009, 30(6):717-721(in Chinese).
[12] TANG X M, WANG J P, SHAO Y T. Three-dimensional numerical investigations of the rotating detonation engine with a hollow combustor[J]. Combustion and Flame, 2014, 162(4):997-1008.
[13] ZHOU R, WANG J P. Numerical investigation of flow particle paths and thermodynamic performance of continuously rotating detonation engines[J]. Combustion and Flame, 2012, 159(12):3632-3645.
[14] ZHOU R, WANG J P. Numerical investigation of shock wave reflections near the head ends of rotating detonation engines[J]. Shock Waves, 2013, 23(5):461-472.
[15] WU D, ZHOU R, LIU M, et al. Numerical investigation on the stability of rotating detonation engine[J]. Combustion Science and Technology, 2014, 186(10-11):1699-1715.
[16] PAN Z H, FAN B C, ZHANG X D, et al. Wavelet pattern and self-sustained mechanism of gaseous detonation rotating in a coaxial cylinder[J]. Combustion and Flame, 2011, 158(11):2220-2228.
[17] LENTSCH A, BEC R, SERRE L, et al. Overview of current french activities on PDRE and continuous detonation wave rocket engines:AIAA-2005-3232[R]. Reston:AIAA, 2005.
[18] DAVIDENKO D M, EUDE Y, GOKALP I. Theoretical and numerical studies on continuous detonation wave engines:AIAA-2011-2334[R]. Reston:AIAA, 2011.
[19] NAPLES A, HOKE J, KARNESKY J, et al. Flowfield characterization of a rotating detonation engine:AIAA-2013-0278[R]. Reston:AIAA, 2013.
[20] SCHWER D A, KAILASANATH K. Modeling exhaust effects in rotating detonation engines:AIAA-2012-3943[R]. Reston:AIAA, 2012.
[21] LIU M, ZHOU R, WANG J P. Numerical investigation of different injection patterns in rotating detonation engines[J]. Combustion Science and Technology, 2015, 187(3):343-361.
[22] SWIDERSKI K, FOLUSIAK M, LUKASIK B, et al. Three dimensional numerical study of the propulsion system based on rotating detonation using adaptive mesh refinement, ICDERS_0133[C]//24th International Colloquium on the Dynamics of Explosions and Reactive Systems, 2013.
[23] FROLOV S M, DUBROVSKII A V, IVANOV V S. Three-dimensional numerical simulation of the operation of a rotating-detonation chamber with separate supply of fuel and oxidizer[J]. Combustion, Explosion and Shock Waves, 2013, 32(2):56-65.
[24] LI X P, WU K, YAO W, et al. A comparative study of highly underexpanded nitrogen and hydrogen jets using large eddy simulation[J]. International Journal of Hydrogen Energy, 2016, 41(9):5151-5161.
[25] YAO W, WANG J, LU Y, et al. Full-scale detached eddy simulation of kerosene fueled scramjet combustor based on skeletal mechanism:AIAA-2015-3579[R]. Reston:AIAA, 2015.
[26] KURGANOV A, TADMOR E. New high-resolution central schemes for nonlinear conservation laws and convection-diffusion equations[J]. Journal of Computational Physics, 2000, 160(1):241-282.
[27] CHASE, M W. JANAF thermochemical tables[J]. Journal of Physical and Chemical Reference Data, 1974, 3(2):311-480.
[28] CHAKRAVARTHY V, MENON S. Large eddy simulations of turbulent premixed flames in the flamelet regime[J]. Combustion Science and Technology, 2001, 162(1):175-222.
[29] WILSON G J, MACCORMACK R W. Modeling supersonic combustion using a fully implicit numerical method[J]. AIAA Journal, 1992, 30(4):1008-1015.

E-mail：hkxb@buaa.edu.cn

关于我们

期刊社服务

专业学科

封面文章

友情链接

主管单位：中国科学技术协会主办单位：中国航空学会北京航空航天大学

连续旋转爆轰发动机冷流场的混合特性研究

Numerical investigation of mixing characteristic of cold continuously rotating detonation engine

PDF (PC)

可视化

摘要/Abstract

引用本文

使用本文

参考文献

相关文章 15

编辑推荐

Metrics

本文评价

[1]	施方成, 高振勋, 田雨岩, 蒋崇文, 王田天, 李椿萱. 超声速理想膨胀喷流噪声的大涡模拟[J]. 航空学报, 2023, 44(2): 626266-626266.
[2]	束珺, 徐东光, 韩志熔, 李斯, 黄雄. 结冰风洞过冷大水滴试验中混合翼设计[J]. 航空学报, 2023, 44(1): 627182-627182.
[3]	赵宾宾, 张恒, 李杰. 翼型结冰状态复杂分离流动数值模拟综述[J]. 航空学报, 2023, 44(1): 627211-627211.
[4]	马乙楗, 柴得林, 王强, 易贤, 孔满昭. 翼面结冰过程中的冰晶运动相变与黏附特性[J]. 航空学报, 2023, 44(1): 627817-627817.
[5]	尧少波, 蒋励剑, 赵文文, 卢铮, 吴昌聚, 陈伟芳. 耦合聚类的数据驱动稀薄流非线性本构计算方法[J]. 航空学报, 2022, 43(S2): 40-53.
[6]	朱炳杰, 杨希祥, 宗建安, 邓小龙. 分布式混合电推进飞行器技术[J]. 航空学报, 2022, 43(7): 25556-025556.
[7]	黄平, 卜雪琴, 刘一鸣, 林贵平, 杨坤. 混合相/冰晶条件下的结冰研究综述[J]. 航空学报, 2022, 43(5): 25178-025178.
[8]	宗建安, 朱炳杰, 侯中喜, 杨希祥. 固旋翼垂直起降混电飞行器推进系统设计[J]. 航空学报, 2022, 43(5): 225395-225395.
[9]	胡嘉欣, 芮姝, 高瑞朝, 苟建军, 龚春林. 飞行器结构布局与尺寸混合优化方法[J]. 航空学报, 2022, 43(5): 225363-225363.
[10]	张钧铎, 左青海, 林孟达, 黄伟希, 潘卫军, 崔桂香. ARJ21飞机尾涡在侧风条件下的近地演化数值模拟[J]. 航空学报, 2022, 43(5): 125043-125043.
[11]	周纬, 杨明绥, 马威. 一种基于麦克风阵列用于分离单极子和偶极子声源的方法[J]. 航空学报, 2022, 43(2): 124901-124901.
[12]	李宁, 刘志勇, 王娜, 杨垒. 基于DUEA的天线伺服控制系统仿真[J]. 航空学报, 2022, 43(2): 324986-324986.
[13]	姜丽红, 饶寒月, 兰夏毓, 杨体浩, 耿建中, 白俊强. 混合层流机翼气动设计与综合收益影响[J]. 航空学报, 2022, 43(11): 526791-526791.
[14]	杨体浩, 白俊强, 段卓毅, 史亚云, 邓一菊, 周铸. 喷气式客机层流翼气动设计综述[J]. 航空学报, 2022, 43(11): 527016-527016.
[15]	赵彦, 段卓毅, 丁兴志, 杨体浩, 王猛. 面向飞行试验的混合层流机翼优化设计[J]. 航空学报, 2022, 43(11): 527539-527539.