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학술연구/단체지원/교육 등 연구자 활동을 지속하도록 DBpia가 지원하고 있어요.
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논문 기본 정보
- 자료유형
- 학술대회자료
- 저자정보
- 발행연도
- 2019.5
- 수록면
- 701 - 712 (12page)
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초록· 키워드
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Rotating detonation engines (RDEs) have been extensively investigated recently as a candidate for an air-breathing propulsive system with high thermal efficiency, with most of the studies focusing on premixed combustion under stoichiometric conditions. Because a purely stoichiometric condition cannot be ascertained in realistic applications, the knowledge of the effects of equivalence ratio becomes very important. The present study has the objective of investigating the effects of equivalence ratio on premixed combustion in a realistic RDE system. For this purpose, both one-dimensional and two-dimensional spatial models are studied. The effects on the pressure, temperature, and chemical species distributions will be presented.
A basic RDE is shown in Fig. 1. The combustion chamber is an annular ring, where the direction of flow is from the head end (bottom in figure) to the exit plane (top of figure). In experimental study, the fuel and oxidizer are injected separately into the combustion chamber to avoid backfire [2]. The mixing process occurs inside the combustion chamber while detonation wave propagates circumferentially to consume fresh reactive mixture.
Schwer et al. [2] investigated the flow field of RDE in general and observed the effect of stagnation and back pressure on an RDE. In addition, Schwer et al.[3] also examined the fluid dynamics of rotating detonation engines with hydrogen and hydrocarbon fuels. Jin Zhou et al.[4] studied the effects of injection nozzle exit width on rotating detonation engine. These studies pertain to stoichiometric conditions. Only a handful of studies have investigated the effects of equivalent ratio. Wang et al.[5] recently investigated the effects of equivalence ratio and found that as the equivalence ratio increases, the velocity of the rotating detonation wave first increases and then decreases. Baoxing et al [6] experimentally studied the effects of equivalence ratio on RDE and found that for their engine model operating with equivalence ratio from 0.42 to 1.43, the rotating detonation wave was successfully initiated, and propagation self-sustained. In this study, we are interested to see how equivalence ratio influence RDE flow field in general. Furthermore, we want to see how it affects the detonation wave structure Key Words: Rotating Detonation Engine, Computational Fluid Dynamics (CFD), Supersonic Combustion, Equivalence Ratio.
A basic RDE is shown in Fig. 1. The combustion chamber is an annular ring, where the direction of flow is from the head end (bottom in figure) to the exit plane (top of figure). In experimental study, the fuel and oxidizer are injected separately into the combustion chamber to avoid backfire [2]. The mixing process occurs inside the combustion chamber while detonation wave propagates circumferentially to consume fresh reactive mixture.
Schwer et al. [2] investigated the flow field of RDE in general and observed the effect of stagnation and back pressure on an RDE. In addition, Schwer et al.[3] also examined the fluid dynamics of rotating detonation engines with hydrogen and hydrocarbon fuels. Jin Zhou et al.[4] studied the effects of injection nozzle exit width on rotating detonation engine. These studies pertain to stoichiometric conditions. Only a handful of studies have investigated the effects of equivalent ratio. Wang et al.[5] recently investigated the effects of equivalence ratio and found that as the equivalence ratio increases, the velocity of the rotating detonation wave first increases and then decreases. Baoxing et al [6] experimentally studied the effects of equivalence ratio on RDE and found that for their engine model operating with equivalence ratio from 0.42 to 1.43, the rotating detonation wave was successfully initiated, and propagation self-sustained. In this study, we are interested to see how equivalence ratio influence RDE flow field in general. Furthermore, we want to see how it affects the detonation wave structure Key Words: Rotating Detonation Engine, Computational Fluid Dynamics (CFD), Supersonic Combustion, Equivalence Ratio.
목차
ABSTRACT
I. GOVERNING EQUATIONS
II. SIMULATION DETAILS
III. PRELIMINARY RESULTS AND DISCUSSIONS
IV. REFERENCES
V. APPENDIX
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