|Table of Contents|

Unsteady rotating detonation phenomenon of hypergolic propellant in annular combustor(PDF)

《火箭推进》[ISSN:1672-9374/CN:CN 61-1436/V]

Issue:
2023年06期
Page:
55-62，81
Research Field:
目次
Publishing date:

Info

Title:
Unsteady rotating detonation phenomenon of hypergolic propellant in annular combustor
Author(s):
YAN Yu;  WANG Zhicheng;  HU Hongbo;  HONG Liu;  YANG Baoe
Science and Technology on Liquid Rocket Engine Laboratory, Xi'an Aerospace Propulsion Institute, Xi'an 710100, China
Keywords:
rotating detonation;  hypergolic propellant;  annular combustor;  experiment;  unsteady state
PACS:
V231.2
DOI:
-
Abstract:
To investigate the propagation characteristics of rotating detonation waves utilizing hypergolic propellant, the rotating detonation was organized in an annular combustor using methylhydrazine as the fuel and nitrogen tetroxide as the oxidizer, respectively.In the combustor with inner diameter 30 mm and outer diameter 60 mm, twenty-four pairs of impinging injection elements were used with oxidizer orifice 0.4 mm and fuel orifice 0.3 mm.Pressure sensors with low sampling rate and high frequency dynamic pressure sensors were used to record the supply and combustion pressures.The results show that the rotating detonation combustion of hypergolic propellant is highly unstable.The detonation wave strength is not only varying from cycle to cycle, but also changing very fast within one cycle.For the generation and maintenance process of rotational detonation combustion with hypergolic propellant, the external stimulation is not a significant factor, and the combustor geometry, mass flow rate and mixture ratio play more important role at rotating detonation.

References:

[1] 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.
[2] 侯凯宇,贺敏,金鹏飞.未来远程对空导弹发展思考[J].上海航天(中英文),2021,38(3):68-75.
[3] MA J Z,LUAN M Y,XIA Z J,et al.Recent progress,development trends,and consideration of continuous detonation engines[J].AIAA Journal,2020,58(12):4976-5035.
[4] 袁雪强,蒋露欣,张多,等.爆震波通过环形通道传播模式试验研究[J].火箭推进,2021,47(6):101-110.
[5] RANKIN B A,RICHARDSON D R,CASWELL A W,et al.Imaging of OH chemiluminescence in an optically accessible nonpremixed rotating detonation engine[C]//53rd AIAA Aerospace Sciences Meeting.Reston,Virginia:AIAA,2015.
[6] 计自飞,李天琦,张会强.吸气式旋转爆震组合循环发动机性能[J].火箭推进,2021,47(6):86-92.
JI Z F,LI T Q,ZHANG H Q.Performance analysis of rotating detonative airbreathing combined cycle engine[J].Journal of Rocket Propulsion,2021,47(6):86-92.
[7] PENG H Y,LIU S J,LIU W D,et al.Enhancement of ethylene-air continuous rotating detonation in the cavity-based annular combustor[J].Aerospace Science and Technology,2021,115:106842.
[8] FROLOV S M,AKSENOV V S,IVANOV V S,et al.Large-scale hydrogen-air continuous detonation combustor[J].International Journal of Hydrogen Energy,2015,40(3):1616-1623.
[9] BYKOVSKII F A,ZHDAN S A,VEDERNIKOV E F.Continuous spin detonations[J].Journal of Propulsion and Power,2006,22(6):1204-1216.
[10] BYKOVSKII F A,ZHDAN S A,VEDERNIKOV E F.Continuous spin detonation of hydrogen-oxygen mixtures.Annular cylindrical combustors[J].Combustion,Explosion,and Shock Waves,2008,44(2):150-162.
[11] BYKOVSKII F A,ZHDAN S A,VEDERNIKOV E F.Continuous spin detonation of hydrogen-oxygen mixtures.Combustor with an expanding annular channel[J].Combustion,Explosion,and Shock Waves,2008,44(3):330-342.
[12] FOTIA M,SCHAUER F,HOKE J.Experimental study of performance scaling in rotating detonation engines operated on hydrogen and gaseous hydrocarbon fuel[C]//20th AIAA International Space Planes and Hypersonic Systems and Technologies Conference.Reston,Virginia:AIAA,2015.
[13] RANKIN B A,RICHARDSON D R,CASWELL A W,et al.Chemiluminescence imaging of an optically accessible non-premixed rotating detonation engine[J].Combustion and Flame,2017,176:12-22.
[14] YAO S B,WANG J P.Multiple ignitions and the stability of rotating detonation waves[J].Applied Thermal Engineering,2016,108:927-936.
[15] PENG H Y,LIU W D,LIU S J,et al.The effect of cavity on ethylene-air continuous rotating detonation in the annular combustor[J].International Journal of Hydrogen Energy,2019,44(26):14032-14043.
[16] LIU S J,PENG H Y,LIU W D,et al.Effects of cavity depth on the ethylene-air continuous rotating detonation[J].Acta Astronautica,2020,166:1-10.
[17] 郑权,翁春生,白桥栋.倾斜环缝喷孔式连续旋转爆轰发动机试验[J].推进技术,2014,35(4):570-576.
[18] XIA Z J,MA H,GE G Y,et al.Effects of ignition condition on the initiation characteristics of rotating detonation wave in plane-radial structure[J].Acta Astronautica,2020,175:79-89.
[19] ZHONG Y P,WU Y,JIN D,et al.Investigation of rotating detonation fueled by the pre-combustion cracked kerosene[J].Aerospace Science and Technology,2019,95:105480.
[20] MENG H L,XIAO Q,FENG W K,et al.Air-breathing rotating detonation fueled by liquid kerosene in cavity-based annular combustor[J].Aerospace Science and Technology,2022,122:107407.
[21] ANDERSON W S,HEISTER S D,HARTSFIELD C.Experimental study of a hypergolically ignited liquid bipropellant rotating detonation rocket engine[C]//AIAA Scitech 2019 Forum.Reston,Virginia:AIAA,2019.
[22] KAN B,HEISTER S D.Chamber volume effects on hypergolic pulse detonation rocket engine[C]//50th AIAA/ASME/SAE/ASEE Joint Propulsion Conference.Reston,Virginia:AIAA,2014.
[23] KAN B,HEISTER S D.Characterization of injector response in a hypergolic pulse detonation rocket engine[C]//51st AIAA/SAE/ASEE Joint Propulsion Conference.Reston,Virginia:AIAA,2015.
[24] SARDESHMUKH S V,HEISTER S D.Reacting opposed jets ofhypergolic propellants MMH and RFNA[C]//50th AIAA/ASME/SAE/ASEE Joint Propulsion Conference.Reston,Virginia:AIAA,2014.
[25] XUE S J,LIU H J,ZHOU L X,et al.Experimental research on rotating detonation with liquid hypergolic propellants[J].Chinese Journal of Aeronautics,2018,31(12):2199-2205.
[26] 严宇,胡洪波,洪流,等.自燃推进剂旋转爆震燃烧实验研究[J].推进技术,2018,39(9):1986-1993.

Memo

Memo:
-
Last Update: 1900-01-01