Film cooling evaluation of a single array of triangular craters

Халатов, А. А.; Shiju, E; Wang, Dongyun; Борисов, И. И.

doi:10.1016/j.ijheatmasstransfer.2020.120055

Cited by 19 publications

(6 citation statements)

References 13 publications

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“…For the study of film cooling with transverse grooves, a triangular design of the groove at the jet exit was designed by Khalatov et al [15], and the three corners were chamfered.…”

Section: Introductionmentioning

confidence: 99%

Contribution of Different Parameters on Film Cooling Efficiency Based on the Improved Orthogonal Experiment Method

Duan,

Chang,

Chen

et al. 2024

Aerospace

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The use of film cooling technology is one of the most effective ways to minimize the damage to wall materials caused by the high-temperature environment in a ramjet. Optimization of the design to achieve the highest film cooling efficiency on the hot wall is the focus of current research. Due to the large number of parameters affecting the film cooling efficiency and the interactions between them, an improved orthogonal design-of-experiments method is chosen to investigate the contribution of different parameters. Flat plate film cooling and transverse groove film cooling are simulated numerically. The results indicated that the contribution of each parameter is ranked as hole spacing (S/D) > incidence angle > blowing ratio for flat plate film cooling; hole spacing > transverse groove depth > blowing ratio > incidence angle for transverse groove film cooling. The film cooling efficiency is inversely proportional to the size of the flow field area affected by the vortex ring and directly proportional to the size of the vortex intensity. Transverse groove film cooling forms a more complete film in most cases, which is better than flat plate film cooling. Within the scope of this study, a complete film at S/D > 2.0 cannot be generated on the flat plate, which should not be used in ramjet.

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“…For the study of film cooling with transverse grooves, a triangular design of the groove at the jet exit was designed by Khalatov et al [15], and the three corners were chamfered.…”

Section: Introductionmentioning

confidence: 99%

Contribution of Different Parameters on Film Cooling Efficiency Based on the Improved Orthogonal Experiment Method

Duan,

Chang,

Chen

et al. 2024

Aerospace

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show abstract

“…Khalatov et al [19] numerically compared the cooling performance among the circular, hemispherical, and triangular cratered holes and found that the triangular cratered hole shows the highest cooling effectiveness. Khalatov et al [20] further performed a comparison study for the triangular cratered hole, emphasizing the effect of the leading-edge shape. Their numerical results showed that the hole with a concavely curved leading edge improves the cooling effectiveness slightly compared to a straight leading edge.…”

Section: Introductionmentioning

confidence: 99%

“…The flow dynamics of the cylindrical hole embedded in the contoured crater were further analyzed using the large eddy simulation [22]. Note that all the cratered holes [18][19][20][21] were studied under the condition of a small lateral distance of 3D between two adjacent rows (D is the cylindrical hole diameter). An et al [23] proposed a novel contoured cratered hole design with a concavely curved protrusion and a larger streamwise diffusion.…”

Section: Introductionmentioning

confidence: 99%

“…The review of the previous studies indicates that the cratered hole with a concavely curved leading edge provides high cooling effectiveness. Besides, as Khalatov et al [20] suggested, the proper design of the concavely curved leading edge can improve cooling effectiveness. Hence, the current paper focuses on the influence of the protrusion shape of the contoured crater.…”

Section: Introductionmentioning

confidence: 99%

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Effect of protrusion shape on film cooling performance for the cylindrical hole embedded in a contoured crater

2023

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The cratered film-cooling hole is regarded as one of the potential applications with high cooling performance and low cost. This study focuses on the influence of the protrusion shape for the contoured crater embedded in the cylindrical hole. Four protrusion shapes, i.e., arc, rectangle, trapezoid, and triangle, are considered. The cooling effectiveness, flow structure, and aerodynamic loss for the cratered holes at blowing ratios of 0.5-2.5 are obtained using the numerical method with the Shear Stress turbulence model. The numerical results indicate that the arc and triangle protrusion models provide better lateral coolant coverage and higher area-averaged cooling effectiveness at higher blowing ratios, attributed to the ascendant anti-kidney-shaped vortex pair. The rectangle protrusion model provides the lowest area-averaged cooling effectiveness because the kidney-shaped vortex pair dominates the downstream flow field. For the aerodynamic loss, the largest total pressure loss coefficient occurs for the rectangle protrusion model and nearly equivalent values for the other three protrusion models. The contoured cratered holes with arc and triangle protrusions are generally recommended.

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“…In this study, the performance of film cooling was evaluated by considering the temperature difference and blowing ratio between the mainstream flow and cooler gas flow. Over the last decade, numerous studies have reported the enhancement of film cooling towards hole exit, console holes, fan-shaped holes, and laidback fan-shaped holes (Khalatov et al, 2020). This research on advanced film-cooling technology is extremely significant and urgent (An et al, 2017).…”

Section: Introductionmentioning

confidence: 99%

Experimental investigation of the film cooling performance by triangular-shaped thin plates on inclined cylindrical holes

Choi

Kwon

et al. 2022

Front. Energy Res.

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Experimental investigations have been conducted to improve the cooling effectiveness of film-cooling technology. A multiple row of cylindrical holes at the flat surface was considered by inclining the holes at 35° along the streamwise direction. A low-speed wind tunnel with the main flow speed of 10 m/s was devised to create a cross flow at a Reynolds number of 196,167 and five blowing ratios of 0.3, 0.5, 0.7, 1, and 2. The proposed triangular-shaped thin plate and flop at the cylindrical film cooling hole were investigated using flow visualization and thermographic techniques. The resulting cooling performances were also experimentally evaluated and compared with respect to the different film-cooling hole configurations. The typical film cooling hole configuration of cylindrical hole shape shows the cooling effectiveness of 0.1 at blowing ration of 1.0. It should be denoted that this cooling effectiveness is exemplary value of wide range of gas turbine applications. We also experimentally evaluates the cooling effectiveness in order to valid our experimental method. Meanwhile, with triangular-shaped thin plate-flop, the flow detachment is successfully prevented with requiring 8% increase of discharge coefficient. In addition, the film flow is stable even at the distant downstream, resulting in enhanced cooling performance compared to the cylindrical and triangular-shaped thin plate. Consequently, a 242.7% improvement in film cooling effectiveness can be achieved with a triangular-shaped thin plate-flop than with a cylindrical hole owing to its enhanced film coverage.

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Film cooling evaluation of a single array of triangular craters

Cited by 19 publications

References 13 publications

Contribution of Different Parameters on Film Cooling Efficiency Based on the Improved Orthogonal Experiment Method

Contribution of Different Parameters on Film Cooling Efficiency Based on the Improved Orthogonal Experiment Method

Effect of protrusion shape on film cooling performance for the cylindrical hole embedded in a contoured crater

Experimental investigation of the film cooling performance by triangular-shaped thin plates on inclined cylindrical holes

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