Effects of slot injection on detonation wavelet characteristics in a rotating detonation engine

Yan, Chian; Teng, Honghui; Ng, Hoi Dick

doi:10.1016/j.actaastro.2021.02.010

Cited by 49 publications

(4 citation statements)

References 61 publications

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“…The disk-shaped RDE experimental system includes a reactant supply system (2-8, 13, 15), disk-shaped RDEs (1), ignition system (9,13,15), measurement, and data acquisition system (10-12, 14, 16), as shown in Figures 1-3 represent the air and H 2 tanks, which are used to provide the oxidizer and fuel required for detonation. The reducing valve (4) and sonic nozzle (5) are used to control the flow rate of supply pipelines.…”

Section: Methodsmentioning

confidence: 99%

“…Researchers have studied the influence of geometric parameters such as different combustor configurations [10,11], diameters, widths, and injection structures [12][13][14] on Rotating Detonation Wave (RDW) propagation characteristics and engine thrust performance [15] in annular RDE and obtained multiple circumferential rotating detonation modes and axial pulse detonation modes [16,17]. It was found that the RDW propagation mode is greatly affected by the injection structure [18].…”

Section: Introductionmentioning

confidence: 99%

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Effect of Combustor Outlet Geometry on Operating Characteristics of Disk-Shaped Rotating Detonation Engine

Xia,

Ma,

et al. 2023

Aerospace

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A disk-shaped rotating detonation engine with H2/air mixture was tested to identify the impact of combustor outlet geometry on the engine’s operating characteristics. Three combustor outlet diameters and five outlet lengths are employed in the experiments. Results show that with the increase of combustor convergent ratio, the propagation stability of the rotating detonation wave decreases, and the propagation velocity and pressure peak decrease slightly. When the convergent ratio increases to a certain value (1.70 in this study), a “platform zone” with a lower pressure value appears before the sharp rise of the dynamic pressure curve. The propagation mode varies with the increase of mass flow rate at different convergent ratios. As the mass flow rate increases, the wave head number in the combustor increases. But the change rule of propagation mode with mass flow rate is greatly affected by convergent ratio. Increasing the convergent ratio is conducive to the formation of multi-wave modes, and the critical mass flow rate for mode transition drops sharply. When the convergent ratio increases to 1.70, the unstable asymmetric dual-wave mode is obtained. With the increase in the convergent ratio, the engine’s operating range and operating stability decrease significantly. Finally, changing the combustor outlet length has little influence on the engine’s operating characteristics and detonation-wave parameters.

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Section: Methodsmentioning

confidence: 99%

Section: Introductionmentioning

confidence: 99%

Effect of Combustor Outlet Geometry on Operating Characteristics of Disk-Shaped Rotating Detonation Engine

Xia,

Ma,

et al. 2023

Aerospace

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“…With the elimination of the inner column, the hollow chamber can effectively avoids the problem of heat dissipation from the inner wall and takes no consideration of the corresponding cooling measures. The increasing number of studies in recent years (Teng et al, 2020;Wang et al, 2021a;Huang et al, 2021;Yan et al, 2021) foretells that rotating detonation engines will have enormous application prospects in the future.…”

Section: Introductionmentioning

confidence: 99%

Experimental Investigation on Two-Phase Rotating Detonation Fueled by Kerosene in a Hollow Directed Combustor

Xue

Ying²,

Ma³

et al. 2022

Front. Energy Res.

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The operating characteristic of two-phase rotating detonation fueled by kerosene in a hollow combustor with the isolation section is experimentally studied. When the air mass flow rate is 1.5 kg/s, the equivalence ratio is 0.98, and the total temperature of the mixture is 650 K, the stable rotating detonation wave (RDW) is obtained, which verifies the feasibility of the designed two-phase rotating detonation combustor (RDC). It is found that there is a high-frequency oblique shock induced by the upstream rotating detonation wave in the isolation section. A series of experimental tests have been carried out by changing the total temperature of incoming air , which is an important factor affecting the initiation. When the equivalent ratio of reactants is between 0.950–1.152, a stable single-wave detonation is formed. With the increase of equivalent ratio, the time of detonation wave establishment decreases, the intensity and frequency of detonation wave increases, and the temperature of engine tail flame rises. The equivalent chamber pressure Δpφ was defined, and the curve of the performance of the RDC with the equivalent ratio was obtained. The velocity of the RDW increases with the increase of equivalent ratio, and the chamber pressure has an optimal value, a higher or lower equivalent ratio will lead to the decrease of equivalent chamber pressure and the combustion chamber performance.

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“…1,2 The discovery of transitory rotating detonation waves in combustors with a planar structure by Voitsekhovskii et al 3,4 in the 1960s laid the groundwork for the creation of RDEs. In recent years, scholars have conducted extensive and significant research on ignition detonation processes, 5,6 working modes, 7,8 injection and doping, 9,10 flow field structures, 11,12 combustion chamber configurations, 13,14 propulsion performances, 15,16 and other topics. Simultaneously, research institutions have conducted theoretical analyses, numerical simulations, and experimental research based on the rocket type, turbine combination, and ramtype RDEs, as well as the integration of rotating detonation combustors (RDCs) into various propulsion systems.…”

Section: Introductionmentioning

confidence: 99%

Numerical investigation on the interactions between rotating detonation wave complex and planar turbine cascade

Xia

et al. 2022

Energy Science & Engineering

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Due to pressure gain characteristics, the rotating detonation combustor (RDC) can be integrated into gas turbines by further improving the system's performance. The matching of unsteady flows in the RDC and turbine is a key challenge. Here, interactions in an RDC and planar turbine cascade are investigated using the unsteady Reynolds time-averaged Navier-Stokes method. The effects of the blade profiles on interactions between the oblique shock wave (OSW) and turbine cascade are analyzed, and the suppression effect of the turbine cascade on high-frequency pressure oscillations is evaluated. The results show that the OSW interacts with the leading edge, pressure side, suction side, and trailing edge of the turbine stator and rotor blades, which generates complex wave systems in the cascade passage. The opposite propagation direction causes the OSW to be aligned or misaligned with the stator blade. The position of the OSW that operates on the turbine cascade changes, and two different wave system structures appear. The various pitches of the turbine cascade at different blade heights cause differing intensities and propagation directions in the reflected wave as generated by the action of the OSW and turbine cascade and the variable flow fields at different blade heights. The turbine cascade can significantly suppress the high-frequency pressure oscillations, while the pressure amplitude attenuation rate can reach over 80% when the OSW propagates through the turbine cascade. These findings expound on the interaction mechanism between the rotating detonation wave complex and the turbine stator and rotor blades.

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Effects of slot injection on detonation wavelet characteristics in a rotating detonation engine

Cited by 49 publications

References 61 publications

Effect of Combustor Outlet Geometry on Operating Characteristics of Disk-Shaped Rotating Detonation Engine

Effect of Combustor Outlet Geometry on Operating Characteristics of Disk-Shaped Rotating Detonation Engine

Experimental Investigation on Two-Phase Rotating Detonation Fueled by Kerosene in a Hollow Directed Combustor

Numerical investigation on the interactions between rotating detonation wave complex and planar turbine cascade

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