Wavelet pattern and self-sustained mechanism of gaseous detonation rotating in a coaxial cylinder

Pan, Zhenhua; Fan, Baochun; Zhang, Xudong; Gui, Mingyue; Dong, Gang

doi:10.1016/j.combustflame.2011.03.016

Cited by 51 publications

(19 citation statements)

References 13 publications

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“…Semi-analytical and simple 0D models have been developed to evaluate the theoretical performance of RDE, as in [13,14]. Even 15 if parametric studies are more complex with 2D/3D numerical tools, numerical simulations are now commonly used, as in [15,16,17,18,19,14,20,21], because they can depart from too simplifying assumptions and give a deep insight into the flow physics. Most of time the injection of a perfect fuel-oxidizer mixture was considered in the simulations.…”

Section: Introductionmentioning

confidence: 99%

Numerical simulation of a Rotating Detonation with a realistic injector designed for separate supply of gaseous hydrogen and oxygen

2017

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Section: Introductionmentioning

confidence: 99%

Numerical simulation of a Rotating Detonation with a realistic injector designed for separate supply of gaseous hydrogen and oxygen

2017

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“…With the advancement of CFD, achievements have been attained on concerns of engineering and fundamental researches, such as thrust performance [8,9] , thermodynamic analysis [10] , design of chamber configurations [11] , three-dimensional effect [12] , detonation wave structures [13] , the stability of detonation [14] .…”

Section: Introductionmentioning

confidence: 99%

“…Such situation is apt to yield instabilities, and vortex-like structures are usually observed along the slip line. Many investigations have reported such unstable structures [8][9][11][12][13][14][15][16][17] , and it is generally believed that Kelvin-Helmholtz (K-H) instability is responsible for their generation [15][16][17] . Although the wide reference of the phenomenon, detailed explanation and thorough analysis are absent so far according to the authors' knowledge.…”

Section: Introductionmentioning

confidence: 99%

Interpretation of wake instability at slip line in rotating detonation

Liu

Qin

Huang

et al. 2018

International Journal of Computational Fluid Dynamics

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In studies on instabilities of flowfield in rotating detonation, one of the most common concerns is the instability at the slip line originating from the conjunction of the detonation wave and oblique shock. Using Euler equations associated with 7-species-and-8-reaction finite-rate chemical reaction model of hydrogen/air mixtures, further studies are performed to simulate the 2-D rotating detonation, and the flow mechanism of instability at the slip line is investigated in depth. The results show that the distinct wake profile exists at the slip line, which is different from the typical mixing layer. Analysis indicates that the generation of wake is caused by the transition shock between the detonation wave and oblique shock. Because of the wake profile, the vorticity distribution therein appears in a double-layer layout, and different evolutions exist in different vorticity layers. Based on the veloc ity profile across the slip line, the analysis by the linear stability theory is made, and two unstable modes which have different shape profiles and phase velocities are found. Discrete Fourier transformation is utilized to analyze the numerical results, and similar shape profiles are obtained. A general coincidence in velocity of vortex movement is also attained between the theoretical predictions and simulations. Investigations show that the wake instability is responsible for the unstable mechanism, and corresponding unstable structures differs from the canonical ones in typical mixing layers.

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“…Recent computational efforts have shown that stable RDE combustor flow can be realized with high efficiency [15,29,34,41]. Experimental studies have demonstrated that it can be operated for a wide variety of fuels and injection conditions [5,7,19].…”

Section: Introductionmentioning

confidence: 99%

Airbreathing rotating detonation wave engine cycle analysis

Braun

Wilson

et al. 2013

Aerospace Science and Technology

129

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A cycle analysis model for an airbreathing, rotating detonation wave engine (RDE) is presented. The engine consists of a steady inlet system with an isolator which delivers air into an annular combustor. A detonation wave continuously rotates around the combustor with side relief as the flow expands towards the nozzle. A model for the side relief is used to find the pressure distribution around the combustor. Air and fuel enter the combustor when the rarefaction wave pressure behind the detonation front drops to the inlet supply pressure. To create a stable RDE, the inlet pressure is matched in a convergence process with the average combustor pressure by increasing the annulus channel radial width with respect to the isolator channel. Performance of this engine is considered using several parametric studies and compared with rocket-mode computational results. A hydrogen-air RDE reaches a specific impulse of 3800 s and can reach a flight speed of Mach 5.

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Wavelet pattern and self-sustained mechanism of gaseous detonation rotating in a coaxial cylinder

Cited by 51 publications

References 13 publications

Numerical simulation of a Rotating Detonation with a realistic injector designed for separate supply of gaseous hydrogen and oxygen

Numerical simulation of a Rotating Detonation with a realistic injector designed for separate supply of gaseous hydrogen and oxygen

Interpretation of wake instability at slip line in rotating detonation

Airbreathing rotating detonation wave engine cycle analysis

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