Propagation process of H2/air rotating detonation wave and influence factors in plane-radial structure

2018 ◽  
Vol 43 (9) ◽  
pp. 4609-4622 ◽  
Author(s):  
Zhenjuan Xia ◽  
Hu Ma ◽  
Changfei Zhuo ◽  
Changsheng Zhou
Keyword(s):  
Detonation Wave ◽  
Influence Factors ◽  
Propagation Process ◽  
Radial Structure ◽  
Rotating 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.

Propagation characteristics of rotating detonation wave in plane–radial structure with different pressure conditions

2018 ◽  
Vol 233 (7) ◽  
pp. 2378-2392 ◽  
Author(s):  
Zhenjuan Xia ◽  
Hu Ma ◽  
Changfei Zhuo ◽  
Changsheng Zhou
Keyword(s):  
Detonation Wave ◽  
Pressure Ratio ◽  
Stagnation Pressure ◽  
Back Pressure ◽  
Propagation Characteristics ◽  
Flow Parameters ◽  
Radial Structure ◽  
Concave Boundary ◽  
Rotating Detonation ◽  
Peak Value

This paper simulates the propagation characteristics of rotating detonation wave in the plane–radial structure for mixtures of 2H2 + O2 + 3.76N2. Two-dimensional numerical simulation was modeled, and two kinds of typical flow field and corresponding operating range were obtained under various pressure conditions. Due to the influence of curvature, the detonation wave is strengthened near the outer concave boundary and weakened near the inner convex one. The pressure ratio was varied from 1.6 to 10 by varying both stagnation and back pressure for detonation parameters and flow parameters. It is found that these parameters are dependent only on stagnation pressure for higher pressure ratio. While the pressure ratio is low, the back pressure also has an effect on them. The detonation wave height initially increases and then decreases as stagnation pressure increases, and the pressure ratio has a significant effect on it for lower pressure ratio. The inlet block ratio varies slightly from 14% to 21%. The exit average Mach number has small fluctuations between 0.89 and 1.05. The exit supersonic flow ratio varies from 14% to 74%, and the peak value is gained when pressure ratio is 6. The exit pressure amplifying ratio varies from 1.45 to 1.95, and the maximum value is obtained when pressure ratio is 2.5.

Investigation on the propagation process of rotating detonation wave

2017 ◽  
Vol 139 ◽  
pp. 278-287 ◽  
Author(s):  
Li Deng ◽  
Hu Ma ◽  
Can Xu ◽  
Changsheng Zhou ◽  
Xiao Liu
Keyword(s):  
Detonation Wave ◽  
Propagation Process ◽  
Rotating 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.

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