Theoretical and Numerical Studies on Continuous Detonation Wave Engines

2011 ◽  
Author(s):  
Dmitry Davidenko ◽  
Yohann Eude ◽  
Iskender Gokalp ◽  
Francois Falempin
Keyword(s):  
Detonation Wave ◽  
Numerical Studies ◽  
Continuous Detonation

scholarly journals Characteristics of a Non-Premixed Rotating Detonation Combustor Using Natural Gas-Hydrogen Blend at Elevated Air-Preheat Temperature and Backpressure

2018 ◽  
Author(s):  
Arnab Roy ◽  
Donald Ferguson ◽  
Todd Sidwell ◽  
Peter Strakey
Keyword(s):  
Experimental Study ◽  
Natural Gas ◽  
Detonation Wave ◽  
Inlet Temperature ◽  
Operational Mode ◽  
Atmospheric Conditions ◽  
Theoretical Understanding ◽  
Air Inlet ◽  
Continuous Detonation ◽  
Rotating Detonation

Operational characteristics of an air breathing Rotating Detonation Combustor (RDC) fueled by natural gas-hydrogen blends are discussed in this paper. Experiments were performed on a 152 mm diameter uncooled RDC with a combustor to inlet area ratio of 0.2 at elevated inlet temperature and combustor pressure while varying the fuel split between natural gas and hydrogen over a range of equivalence ratios. Experimental data from short-duration (∼6sec) tests are presented with an emphasis on identifying detonability limits and exploring detonation stability with the addition of natural gas. Although the nominal combustor used in this experiment was not specifically designed for natural gas-air mixtures, significant advances in understanding conditions necessary for sustaining a stable, continuous detonation wave in a natural gas-hydrogen blended fuel were achieved. Data from the experimental study suggests that at elevated combustor pressures (2–3bar), only a small amount of natural gas added to the hydrogen is needed to alter the detonation wave operational mode. Additional observations indicate that an increase in air inlet temperature (up to 204°C) at atmospheric conditions significantly affects RDC performance by increasing deflagration losses through an increase in the number of combustion (detonation/Deflagration) regions present in the combustor. At higher backpressure levels the RDC exhibited the ability to achieve stable detonation with increasing concentrations of natural gas (with natural gas / hydrogen-air blend). However, losses tend to increase at intermediate air preheat levels (∼120°C). It was observed that combustor pressure had a first order influence on RDC stability in the presence of natural gas. Combining the results from this limited experimental study with our theoretical understanding of detonation wave fundamentals provides a pathway for developing an advanced combustor capable of replacing conventional constant pressure combustors typical of most power generation processes with one that produces a pressure gain.

Design and Penetration Performance of Annular Shaped Charge Structure

2008 ◽  
Vol 33-37 ◽  
pp. 1175-1180
Author(s):  
Wang Cheng ◽  
Tian Bao Ma ◽  
Jian Guo Ning
Keyword(s):  
Detonation Wave ◽  
Wave Front ◽  
Shaped Charge ◽  
Penetration Process ◽  
Charge Structure ◽  
Detonation Wave Front ◽  
Numerical Studies ◽  
External Charge

Based on the principle of the equivalent momentum of the corresponding elements for internal and external liners, annular shaped charge structure is proposed. The generatrix analytical equations for the external surfaces of the external liner and external charge are deduced. Experimental and numerical studies are conducted to investigate the formation and penetration process of the jet for the annular shaped charge under different initiation radiuses, and the initiation radius corresponding to the detonation wave front matched with the liner is optimized. At this radius, shaped charge can form an ideal cylindrical jet. Moreover, the diameter of the jet approximates the theoretical diameter of the jet, and has satisfactory symmetry and focus.

scholarly journals Numerical investigation of an unsteady injection adapted to the continuous detonation wave rocket engine operation

2019 ◽  
Author(s):  
T. Gaillard ◽  
D. Davidenko ◽  
F. Dupoirieux
Keyword(s):  
Detonation Wave ◽  
Rocket Engine ◽  
Three Dimensional ◽  
Mixing Efficiency ◽  
Thermodynamic Efficiency ◽  
Engine Operation ◽  
Injection Process ◽  
Continuous Detonation ◽  
Set Up ◽  
Separate Injection

Detonation applied to propulsion could result in a promising increase of the thermodynamic efficiency of the engine cycle. Numerical simulations of the detonation propagating in the Continuous Detonation Wave Rocket Engine (CDWRE) are currently performed but still do not account for realistic injection process. The assumption of an ideal injected premix is generally chosen for convenience to obtain theoretical results. Comparison of the numerical results with experiments is difficult because of the clear difference of the injection configurations. Some physical aspects of the separate injection of the components used in experiments are not clearly assessed. This study is included in a wider numerical project aimed at designing and optimizing a realistic CDWRE. The optimization process is presently focused on the injector. One element of the injection hole pattern is considered assuming that this element is periodically repeated over the injector head. The aim of the work presented here is to model and analyze the refill process of the components in the combustion chamber behind the rotating detonation. The simulation starts just after the passage of the detonation over the considered injection element. This simulation gives information on the way the injected propellants recreate the reactive mixture for the next detonation. In the first step, two-dimensional (2D) computations helped us to set up the methodology and to study the dynamic response of the fresh components injected. A comparison between 2D homogeneous and separate injections is provided. In the second step, three-dimensional (3D) computations have been performed with a separate injection suitable for the CDWRE operation. Some performance parameters are evaluated such as mixing efficiency or filling of the domain.

NUMERICAL INVESTIGATION OF THE INFLUENCE OF WATER DROPS ON THE STRUCTURE OF A DETONATION WAVE IN THE METHANE-AIR MIXTURE

2020 ◽  
Author(s):  
V. Yu. Gidaspov ◽  
◽  
O. A. Moskalenko ◽  
N. S. Severina ◽  
Ch. Fang ◽  
...  
Keyword(s):  
Detonation Wave ◽  
Numerical Investigation ◽  
Water Injection ◽  
Detonation Waves ◽  
Effect Of Water ◽  
Numerical Studies ◽  
Influence Of Water ◽  
Water Drops ◽  
Combustible Mixtures

The results of numerical studies of the effect of water injection on the parameters of detonation waves in gas combustible mixtures are presented.

Design of a Continuous Detonation Wave Engine for Space Application

2006 ◽  
Author(s):  
Emeric Daniau ◽  
Francois Falempin ◽  
N. Getin ◽  
Fedor Bykovskii ◽  
Sergey Zhdan
Keyword(s):  
Detonation Wave ◽  
Space Application ◽  
Continuous Detonation

scholarly journals Effects of Diverging Nozzle Downstream on Flow Field Parameters of Rotating Detonation Combustor

2019 ◽  
Vol 9 (20) ◽  
pp. 4259 ◽  
Author(s):  
Chengwen Sun ◽  
Hongtao Zheng ◽  
Zhiming Li ◽  
Ningbo Zhao ◽  
Lei Qi ◽  
...  
Keyword(s):  
Detonation Wave ◽  
Flow Field ◽  
Three Dimensional ◽  
Great Influence ◽  
Working Environment ◽  
Propagation Process ◽  
High Pressure And Temperature ◽  
Numerical Studies ◽  
Temperature Load ◽  
Rotating Detonation

In this study, three-dimensional numerical studies have been performed to investigate the performance of a rotating detonation combustor with a diverging nozzle downstream. The effects of a diverging nozzle on the formation and propagation process of a detonation wave and typical flow field parameters in a rotating detonation combustor are mainly discussed. The results indicate that the diverging nozzle downstream is an important factor affecting the performance and design of a rotating detonation combustor. The diverging nozzle does not affect the formation and propagation process of the rotating detonation wave, while the time of two key wave collisions are delayed during the formation process of the detonation wave. With increases of the diverging angle, the rotating detonation combustor with the diverging nozzle can still maintain a certain pressure gain performance. Both the diverging nozzle and diverging angle have great influence on the flow field parameters of the rotating detonation combustor, including reducing the high pressure and temperature load, making the distribution of the outlet parameters uniform, and changing the local supersonic flow at the outlet. Among them, the outlet static pressure is reduced by up to 88.32%, and the outlet static temperature is reduced by up to 32.12%. This evidently improves the working environment of the combustor while reducing the thermodynamic and aerodynamic loads at the outlet. In particular, the diverging nozzle does not affect the supersonic characteristics of the outlet airflow, and on this basis, the Mach number becomes coincident and enhanced.

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