Numerical investigation on flow and film cooling characteristics of coolant injection in rotating detonation combustor

Jia, Tian; Wang, Yuan-shuai; Zhang, Jingzhou; Tan, Xiaoming

doi:10.1016/j.ast.2022.107379

Cited by 25 publications

(3 citation statements)

References 34 publications

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“…The research on effective cooling schemes for the chamber walls of the rotating detonation engine (RDE) is currently limited, despite the reported high-frequency heat flux experienced by these walls [16,17]. A widely used cooling technique in conventional gas turbines, known as film cooling, has been numerically verified and proven effective [18,19]. Nevertheless, the existing studies still focused on RDEs using gaseous fuels instead of the more practical liquid fuels such as kerosene; there are, however, notable distinctions between gaseous and two-phase rotating detonation waves.…”

Section: Introductionmentioning

confidence: 99%

Analysis of the flow field of kerosene-fueled rotating detonation engine with film cooling

Li,

Yu,

et al. 2024

J. Phys.: Conf. Ser.

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The advance of the rotating detonation engine (RDE) toward practical applications demands the integration of effective cooling schemes. In this study, a three-dimensional simulation of the hydrogen-enhanced kerosene-air RDE with inclined cylindrical film cooling holes is conducted to analyze the influence of the cooling flow on the two-phase rotating detonation flow field based an Eulerian–Lagrangian model. The liquid kerosene is injected at the ambient temperature with hydrogen-assisted combustion enhancement. Results suggest that a stable propagation of the kerosene-fueled rotating detonation wave can be maintained after the introduction of cooling air and the three-dimensional structure of the flow field is analyzed. It is found that the periodic sweeping action of the detonation wave leads to temporary blockages of the film cooling holes, causing interruptions in the outflow of cooling air. Additionally, the investigation highlights the intensified heating and evaporation of kerosene droplets near the outer wall of the RDE, whereas the presence of cooling air prevents the accumulation of kerosene vapor near the outer wall. It is revealed that the film cooling efficiency exhibits a lower value in the vicinity of the fuel injection surface, but gradually increases along the length of the combustion chamber.

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Section: Introductionmentioning

confidence: 99%

Analysis of the flow field of kerosene-fueled rotating detonation engine with film cooling

Li,

Yu,

et al. 2024

J. Phys.: Conf. Ser.

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“…Many scholars have conducted a large number of studies on the effect of film cooling on flat plates [19][20][21][22][23], and the research results show that the blow ratio, hole inclination angle, and the shape of film holes are important factors affecting the effect of film cooling. Film cooling technology has shown excellent cooling effects in the cooling of engine components such as turbine blades [24][25][26], combustion chambers [27,28], and other hot sections. Therefore, exploring and studying the effects of applying film cooling technology to an axisymmetric plug nozzle is worthwhile.…”

Section: Introductionmentioning

confidence: 99%

Investigation on the Influence of Film Cooling Structure on the Flow and Heat Transfer Characteristics of Axisymmetric Plug Nozzle

Ma,

Zhang,

Bai

2024

Symmetry

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Some numerical simulations were used to study the effects of blowing ratio (0.25–0.5), hole diameters(0.65~1 mm), and hole inclination angle (30~60°) of the film cooling structure on the cooling and aerodynamic characteristics of the axisymmetric plug nozzle under the condition of transonic. The results showed that the bow shocks appear near the film holes on the plug wall in the supersonic region, which cause the wall cooling effectiveness of the plug to decrease. Compared with the baseline plug, the blowing ratio ranged from 0.25 to 0.5, the wall average temperature of the rear plug decreased by 34.4~48.1%, the thrust coefficient and total pressure recovery coefficient decreased by 0.31~0.61% and 0.52~0.93%, respectively. When the perforated percentage is constant, the wall cooling effectiveness increases with the decrease of the hole diameters. The increase in the inclination angle of the film holes lead to the decrease in cooling effectiveness and aerodynamic performance. This is because the penetration ability of the cooling air to the mainstream is enhanced, and the obstruction to the mainstream boundary layer is increased, resulting in the increase of bow shock intensity near the film holes in the supersonic region.

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“…Cooling film would form on the outer wall of the RDE and they managed to control the outer wall temperature within 850 K; however, the possible effects on the structure and propagation of the RDW were not reported in details. In a numerical study of Tian et al [41], the interactions between the secondary flow from film cooling and the RDW was investigated. It was found that the secondary flow would oscillate periodically and the cooling effect was most significant on the downstream region swept by the oblique shock wave.…”

Section: Introductionmentioning

confidence: 99%

Effects of inlet and secondary flow conditions on the flow field of rotating detonation engines with film cooling

Yao

et al. 2023

International Journal of Hydrogen Energy

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Numerical investigation on flow and film cooling characteristics of coolant injection in rotating detonation combustor

Cited by 25 publications

References 34 publications

Analysis of the flow field of kerosene-fueled rotating detonation engine with film cooling

Analysis of the flow field of kerosene-fueled rotating detonation engine with film cooling

Investigation on the Influence of Film Cooling Structure on the Flow and Heat Transfer Characteristics of Axisymmetric Plug Nozzle

Effects of inlet and secondary flow conditions on the flow field of rotating detonation engines with film cooling

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