Secondary shock wave in rotating detonation combustor

被引：13

作者：

Deng, Li ^{[1
]}

Ma, Hu ^{[2
]}

Liu, Xiao ^{[3
]}

Zhou, Changsheng ^{[2
]}

机构：

[1] China Acad Engn Phys, Inst Chem Mat, Mianyang 621900, Sichuan, Peoples R China

[2] Nanjing Univ Sci & Technol, Sch Mech Engn, Nanjing 210094, Jiangsu, Peoples R China

[3] Harbin Engn Univ, Coll Power & Energy Engn, Harbin 150001, Heilongjiang, Peoples R China

来源：

AEROSPACE SCIENCE AND TECHNOLOGY | 2019年 / 95卷

基金：

中国国家自然科学基金;

关键词：

Rotating detonation combustor; Secondary shock wave; Pseudo-nozzle flow; Over-expansion; Chamber length; Double-wave collision; NUMERICAL SIMULATIONS; AIR; INITIATION; PERFORMANCE; TRANSITION; DYNAMICS; MODE; FLOW;

D O I：

10.1016/j.ast.2019.105517

中图分类号：

V [航空、航天];

学科分类号：

08 ; 0825 ;

摘要：

The secondary shock wave in rotating detonation combustor is studied by the combination of numerical simulation and experiments. Based on the pseudo-nozzle flow in the post-detonation zone, the influencing factors which cause the existence of secondary shock wave are clarified and then verified by experiments. The results show that the secondary shock wave is caused by the over-expansion of detonation products. An increase in the ratio of stagnation pressure over backpressure, or inlet mass flux reduces the degree of products expansion, and in turn alleviates or eliminates the occurrence of the secondary shock wave. However, the experimental results show that the increase of combustor length leads to the occurrence of double-wave collision under the case of low mass flow rate. The interactions between the remnant hot products and the reflection of secondary shock wave at the injection plane are supposed to the mechanism of the mode transition. (C) 2019 Elsevier Masson SAS. All rights reserved.

引用

页数：15

共 53 条

[1] Longitudinal pulsed detonation instability in a rotating detonation combustor [J].

Anand, Vijay ;

George, Andrew St. ;

Driscoll, Robert ;

Gutmark, Ephraim .

EXPERIMENTAL THERMAL AND FLUID SCIENCE, 2016, 77 :212-225

[2] Characterization of instabilities in a Rotating Detonation Combustor [J].

Anand, Vijay ;

St George, Andrew ;

Driscoll, Robert ;

Gutmark, Ephraim .

INTERNATIONAL JOURNAL OF HYDROGEN ENERGY, 2015, 40 (46) :16649-16659

[3] High-speed imaging of wave modes in an RDC [J].

Bohon, M. D. ;

Bluemner, R. ;

Paschereit, C. O. ;

Gutmark, E. J. .

EXPERIMENTAL THERMAL AND FLUID SCIENCE, 2019, 102 :28-37

[4] Experimental investigation of detonation quenching in non-uniform compositions [J].

Boulal, Stephane ;

Vidal, Pierre ;

Zitoun, Ratiba .

COMBUSTION AND FLAME, 2016, 172 :222-233

[5] Continuous detonation of a subsonic flow of a propellant [J].

Bykovskii, FA ;

Vedernikov, EF .

COMBUSTION EXPLOSION AND SHOCK WAVES, 2003, 39 (03) :323-334

[6] Continuous spin detonations [J].

Bykovskii, Fedor A. ;

Zhdan, Sergey A. ;

Vedernikov, Evgenii F. .

JOURNAL OF PROPULSION AND POWER, 2006, 22 (06) :1204-1216

[7] Detonability limits in thin annular channels [J].

Chao, J. ;

Ng, H. D. ;

Lee, J. H. S. .

PROCEEDINGS OF THE COMBUSTION INSTITUTE, 2009, 32 :2349-2354

[8] Computational fluid dynamics algorithms for unsteady shock-induced combustion, part 1: Validation [J].

Choi, JY ;

Jeung, IS ;

Yoon, YB .

AIAA JOURNAL, 2000, 38 (07) :1179-1187

[9]

Cocks P. A., 2016, 54 AIAA AER SCI M

[10] The feasibility of mode control in rotating detonation engine [J].

Deng, Li ;

Ma, Hu ;

Xu, Can ;

Liu, Xiao ;

Zhou, Changsheng .

APPLIED THERMAL ENGINEERING, 2018, 129 :1538-1550

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