Experimental Study of the Disk-Shaped Rotating Detonation Turbine Engine

Higashi, Junichi; Ishiyama, Chikara; Nakagami, Soma; Matsuoka, K.; Kasahara, Jiro; Matsuo, Akiko; Funaki, Ikkoh; Moriai, Hideki

doi:10.2514/6.2017-1286

Cited by 28 publications

(6 citation statements)

References 4 publications

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“…Higashi et al [30] and Rhee et al [31] describe two experiments conducted at Nagoya University. Higashi et al coupled a centrifugal compressor, a radial-outward combustor and a radial turbine on one side of a rotor disk.…”

mentioning

confidence: 99%

Performance analysis of a rotating detonation combustor based on stagnation pressure measurements

Bach

Stathopoulos

Paschereit

et al. 2020

Combustion and Flame

105

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mentioning

confidence: 99%

Performance analysis of a rotating detonation combustor based on stagnation pressure measurements

Bach

Stathopoulos

Paschereit

et al. 2020

Combustion and Flame

105

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“…Based on the research above, Ishiyama [41] and Huff [42] proposed the concept of a rotating detonation turbine engine, including a centrifugal compressor, a disk-shaped combustor, and a radial flow turbine. Several combustion modes in C2H4/O2 mixture were obtained, and the phenomena of detonation decoupling and re-initiation were observed in the combustor [43]. The RDW propagation processes under different combustor channel heights and injection conditions were also studied and obtained that increasing mass flux produced more power and more efficiency for turbine RDE [42].…”

Section: Introductionmentioning

confidence: 97%

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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“…It is found that when the air is preheated, the engine can obtain a stable detonation state, which is 5% -7% higher than the traditional combustion thermal efficiency. Ishiyama and Higashi et al [7] [8] designed to connect the RDC with a single-stage centrifugal compressor and a single-stage radial turbine. During the test, phenomena such as detonation wave number, extinction and restart of combustion were observed, and the detonation wave propagation speed was 25% -45% of CJ speed.…”

Section: Introductionmentioning

confidence: 99%

Three-dimensional numerical study on the interaction between RDC and NGV

Xue

Yang²,

Liu³

et al. 2023

J. Phys.: Conf. Ser.

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In this paper, the three-dimensional numerical method is used to study the change of the internal flow field distribution characteristics of a RDC with a deflector installed at the outlet, using the premixed gas of kerosene and air as reactants. It is found that the total pressure in the front section of the combustor has been improved. Different configurations of deflectors were designed. It was found that the flow field in the combustion chamber could not be significantly changed by changing the number of blades, but the maximum average total pressure and the total pressure loss in the mixing section could be effectively improved by adjusting the angle of incidence. Because the propagation direction of rotating detonation wave and the deflector blade have directionality, the study found that when the two directions are opposite, the reflected shock wave formed at the inlet of the deflector changes greatly, the working environment of the fixed blade is worse, the uniformity of gas after passing the deflector decreases, the flow field along the axial average total pressure loss increases significantly, and the peak value of the total pressure shifts significantly downstream. The study of the interaction between NGV and RDC provides a basis for the design of the rotaing detonation turbine engine.

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Experimental Study of the Disk-Shaped Rotating Detonation Turbine Engine

Cited by 28 publications

References 4 publications

Performance analysis of a rotating detonation combustor based on stagnation pressure measurements

Performance analysis of a rotating detonation combustor based on stagnation pressure measurements

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

Three-dimensional numerical study on the interaction between RDC and NGV

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