Micro film cooling performance

Li, P. L.; Ko, H. S.; Jeng, D. Z.; Liu, C. W.; Gau, Chie

doi:10.1016/j.ijheatmasstransfer.2009.08.011

Cited by 10 publications

(6 citation statements)

References 12 publications

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“…• The Experimental work from Li et al [14] followed a novel idea in increasing the film cooling performance by varying the height of a micro slot and found that the micro-scale film performed better than the macro-scale film cooling.…”

Section: Advancement In Film Cooling Technologymentioning

confidence: 99%

“…An attempt for increasing the performance of film cooling was mainly focused on the experimental and computational works mentioned above and was found that decrease in coolant hole exit area increased the performance with minimum amount of coolant usage. The micro jet from the slot had deeper penetration into the mainstream flow without mixing which resulted in better cooling performance than the macro jet film [14] . The micro jets maintained its structure without breakdown and provided better cooling performance in immediate vicinity region of the coolant hole.…”

Section: Advancement In Film Cooling Technologymentioning

confidence: 99%

“…The behaviour of micro flow in film cooling has been mentioned by some of the studies mentioned previously in section 1.3.1. The experimental study of Li et al [14] found that the performance of micro film cooling was based on height of the slot. The use of smaller slot height results in better performance and smaller amount of coolant is used than the larger slot.…”

Section: Micro Flow Behaviourmentioning

confidence: 99%

“…Sriram and Jagadeesh [13] experimentally studied the application of micro-jet in the front face of blunt body results in better effectiveness and the jet travels long distance without getting mixed with the mainstream air. An another experimental work from Li et al [14] on micro slot cooling determines that the flow from micro slot travels longer distance than macro slot jet without break and achieve better effectiveness by the use of a minimum amount of coolant. The above investigations report that the improvement in film cooling performance was due to reduction in the coolant exit area.…”

Section: Introductionmentioning

confidence: 99%

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Numerical Analysis of Film Cooling from Micro-Hole

Balasubrammaniyan¹

2021

Preprint

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The performance of aircraft gas turbine engines mainly depends on performance of the turbine which expands the combusted air into the atmosphere. The turbine is a critical part which gets affected by the hot gas from combustor exhaust. So in order to enhance the performance of gas turbine engines, a proposed cooling type called film cooling is used for more than six decades. The current work is also an attempt to enhance the performance of the gas turbine engine by enhancing the film cooling performance. The film cooling performance was numerically calculated on a flat plate with micro-hole and compared the cooling performance from the macro-hole. The analysis was carried out for different blowing ratios and found that the coolant from micro-hole performs better in the vicinity region and also spreads well in the lateral direction. The vortex structure is also captured from the proposed turbulence model and discussed. The behaviour of micro flow inside the coolant pipe was also analyzed. The comparison between multiple micro-hole jets and discrete jets was also made and discussed.

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Section: Advancement In Film Cooling Technologymentioning

confidence: 99%

Section: Advancement In Film Cooling Technologymentioning

confidence: 99%

Section: Micro Flow Behaviourmentioning

confidence: 99%

Section: Introductionmentioning

confidence: 99%

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Numerical Analysis of Film Cooling from Micro-Hole

Balasubrammaniyan¹

2021

Preprint

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“…Li et al [19] experimentally studied film cooling effectiveness from a micro slot at different slot heights of 25 µm, 45 µm, and 50 µm on a flat plate at blowing rates M=(1 -12.5).…”

Section: Micro Hole Film Coolingmentioning

confidence: 99%

Numerical Analysis of Film Cooling Performance of Micro Holes and Compound Angle Sister Holes

Alsalam¹

2021

Preprint

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In the present research, micro holes and compound angle sister holes have been numerically investigated as two different techniques to enhance the cylindrical hole cooling performance, which suffers from a low cooling performance at high blowing ratio. The numerical analysis is performed over a flat plate model to assess the film effectiveness and the associated flow field at low and high blowing ratios. The performance assessment of the discrete round micro hole with a 200 µm diameter reveals that the micro hole yields the best cooling performance at low blowing ratios, and there is nearly 30% increase in the overall film cooling effectiveness compared to that of the round macro hole. The flow field results demonstrate the presence of a Counter-Rotating Vortex Pair (CRVP) at a smaller size and less strength, thus, contributed to better spanwise spreading of the coolant jet and lateral film cooling effectiveness. Micro holes present an improvement in the lateral film cooling effectiveness at high freestream turbulence intensity and high blowing ratios. Computational evaluation of the CFD prediction capability of the sister holes cooling effectiveness using five RANS turbulence models has been carried out as well as an assessment of the effects of the near-wall modeling on the predicted lateral effectiveness. The turbulence models used are realizable k-epsilon, standard k-epsilon, RNG k-epsilon, Reynolds stress model, and Spalart-Allmaras model. It is generally found that realizable k-ε combined with the enhanced wall treatment provides the best prediction of the numerical results in comparison to the experimental measurements at a low blowing ratio while an underprediction of the lateral performance is found at a high blowing ratio from all examined turbulence models. The compound angle upstream sister holes (CAUSH) have been proposed as a novel and simple design of the cooling hole whereas the numerical results have shown a notable increase in both centerline and lateral effectiveness for all tested compound angles at all blowing ratios. The anti-counter rotating vortices pair (ACRVP) structure generated from the compound angle upstream sister holes has actively controlled the flow field and maintained the coolant jet fully attached to the plate surface while restraining the coolant lift-off at high blowing ratios. Finally, the influence of the compound angle sister holes streamwise location on the thermal and flow field performance has also been analyzed, whereas three locations: upstream, midstream, and downstream are examined. It is found that the midstream and downstream locations offered a considerable increase in the cooling effectiveness, which is very much dependent on the blowing ratio and the area downstream of the cooling holes. In addition, the optimum centerline effectiveness is obtained by the downstream location, while the best lateral effectiveness is attained through the midstream location.

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Numerical Study of the Film Cooling with Micro Jets

Gurjar,

Mishra

2024

Lecture Notes in Mechanical Engineering

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Micro film cooling performance

Cited by 10 publications

References 12 publications

Numerical Analysis of Film Cooling from Micro-Hole

Numerical Analysis of Film Cooling from Micro-Hole

Numerical Analysis of Film Cooling Performance of Micro Holes and Compound Angle Sister Holes

Numerical Study of the Film Cooling with Micro Jets

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