Numerical investigation of the effect of inlet mass flow rates on H2/air non-premixed rotating detonation wave

Meng, Qingyang; Zhao, Ningbo; Zheng, Hongtao; Yang, Jian; Qi, Lei

doi:10.1016/j.ijhydene.2018.05.115

Cited by 45 publications

(9 citation statements)

References 50 publications

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“…Some hurdles include the incomplete fuel-air mixing at the molecular level, the stability of the detonation and the strong noise generated by the system even in highly idealized configurations (Kailasanath 2000(Kailasanath , 2003. Non-idealized configurations representative of more realistic systems may include additional complexities, such as detonation-wall interaction, confinement, turbulence, multi-phase flow and non-perfect mixing, in addition to the complexities that arise in the modelling of chemical kinetics and transport properties (Meng et al 2018).…”

Section: Introductionmentioning

confidence: 99%

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Effect of equivalence ratio fluctuations on planar detonation discontinuities

2020

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Section: Introductionmentioning

confidence: 99%

“…Non-idealized configurations representative of more realistic systems may include additional complexities, such as detonation-wall interaction, confinement, turbulence, multi-phase flow and non-perfect mixing, in addition to the complexities that arise in the modelling of chemical kinetics and transport properties (Meng et al. 2018).…”

Section: Introductionmentioning

confidence: 99%

Effect of equivalence ratio fluctuations on planar detonation discontinuities

2020

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“…Due to the difficulty of the high Mach number environment in the standing oblique detonation combustion process [11] and the high frequency ignition in the pulse detonation combustion process [12], rotating detonation with its wide working range and self-sustaining propagation has been attracting increasing attention. The evolution characteristics of rotating detonation wave [13,14], the thermodynamic characteristics of rotating detonation flow fields [15][16][17][18][19] and the propulsion performance of the rotating detonator combustor (RDC) [20][21][22] have been investigated with a series of experiments and numerical studies.…”

Section: Introductionmentioning

confidence: 99%

Investigation of the Pressure Gain Characteristics and Cycle Performance in Gas Turbines Based on Interstage Bleeding Rotating Detonation Combustion

Wang

Zhao

et al. 2019

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To further improve the cycle performance of gas turbines, a gas turbine cycle model based on interstage bleeding rotating detonation combustion was established using methane as fuel. Combined with a series of two-dimensional numerical simulations of a rotating detonation combustor (RDC) and calculations of cycle parameters, the pressure gain characteristics and cycle performance were investigated at different compressor pressure ratios in the study. The results showed that pressure gain characteristic of interstage bleeding RDC contributed to an obvious performance improvement in the rotating detonation gas turbine cycle compared with the conventional gas turbine cycle. The decrease of compressor pressure ratio had a positive influence on the performance improvement in the rotating detonation gas turbine cycle. With the decrease of compressor pressure ratio, the pressurization ratio of the RDC increased and finally made the power generation and cycle efficiency enhancement rates display uptrends. Under the calculated conditions, the pressurization ratios of RDC were all higher than 1.77, the decreases of turbine inlet total temperature were all more than 19 K, the power generation enhancements were all beyond 400 kW and the cycle efficiency enhancement rates were all greater than 6.72%.

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“…Detonation combustion has attracted plenty of attention from researchers because of its high thermal efficiency, low entropy generation and self-pressurization characteristic [1,2]. According to the formation process of detonation waves and operating characteristics in the engines, detonation engines can be divided into rotating detonation engine (RDE) [3,4], pulse detonation engine (PDE) [5,6] and standing detonation wave engine (SDWE) [7]. The detonation initiation technology is one of the bottlenecks and key technologies that restrict the engineering application of any detonation engines.…”

Section: Introductionmentioning

confidence: 99%

Numerical Simulation of Hot Jet Detonation with Different Ignition Positions

et al. 2019

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Ignition position is an important factor affecting flame propagation and deflagration-to-detonation transition (DDT). In this study, 2D reactive Navier–Stokes numerical studies have been performed to investigate the effects of ignition position on hot jet detonation initiation. Through the stages of hot jet formation, vortex-flame interaction and detonation wave formation, the mechanism of the hot jet detonation initiation is analyzed in detail. The results indicate that the vortexes formed by hot jet entrain flame to increase the flame area rapidly, thus accelerating energy release and the formation of the detonation wave. With changing the ignition position from top to wall inside the hot jet tube, the faster velocity of hot jet will promote the vortex to entrain jet flame earlier, and the DDT time and distance will decrease. In addition, the effect of different wall ignition positions (from 0 mm to 150 mm away from top of hot jet tube) on DDT is also studied. When the ignition source is 30 mm away from the top of hot jet tube, the distance to initiate detonation wave is the shortest due to the highest jet intensity, the DDT time and distance are about 41.45% and 30.77% less than the top ignition.

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Numerical investigation of the effect of inlet mass flow rates on H2/air non-premixed rotating detonation wave

Cited by 45 publications

References 50 publications

Effect of equivalence ratio fluctuations on planar detonation discontinuities

Effect of equivalence ratio fluctuations on planar detonation discontinuities

Investigation of the Pressure Gain Characteristics and Cycle Performance in Gas Turbines Based on Interstage Bleeding Rotating Detonation Combustion

Numerical Simulation of Hot Jet Detonation with Different Ignition Positions

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