Heat transfer for a planar air jet striking a concave surface

Dyban, E. P.; Mazur, A. I.

doi:10.1007/bf00828306

Cited by 13 publications

(6 citation statements)

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“…Metzger et al50 investigated heat transfer of impingement of a row of circular jets on a semi‐circular surface. Dyban and Mazur51 measured heat transfer coefficients on a parabolic concave surface where a slot jet impinged. Several other investigators27,46,52,53 studied the effect of curvature on the impingement heat transfer of a round jet, a slot jet, and a row of round jets.…”

Section: Effects Of Other Parametersmentioning

confidence: 99%

Jet‐Impingement Heat Transfer in Gas Turbine Systems

Han

Goldstein

2001

Annals of the New York Academy of Sciences

177

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A review of jet‐impingement heat transfer in gas turbine systems is presented. Characteristics of the different flow regions for submerged jets ‐ free jet, stagnation flow, and wall jet ‐ are reviewed. Heat transfer characteristics of both single and multiple jets are discussed with consideration of the effects of important parameters relevant to gas turbine systems including curvature of surfaces, crossflow, angle of impact, and rotation.

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Section: Effects Of Other Parametersmentioning

confidence: 99%

Jet‐Impingement Heat Transfer in Gas Turbine Systems

Han

Goldstein

2001

Annals of the New York Academy of Sciences

177

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“…Lately, the focus has moved to include surface heating applications to aid in better understanding and design of hot-air based anti-icing systems. 19–24…”

Section: Introductionmentioning

confidence: 99%

Anti-icing hot air jet heat transfer augmentation employing inner channels

Saeed

Ahmed

Owes

et al. 2021

Advances in Mechanical Engineering

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Many approaches exist today that employ hot-air from aircraft compressor bleed for anti-icing critical aircraft surfaces. This paper introduces and numerically analyzes the novel application of an inner or etched channel to augment heat transfer from a hot-air jet impinging on a curved surface representing the inner surface of an aircraft wing’s leading edge or slat. The study shows that proper positioning, geometry, and flow characteristics of a channel along the inner surface of the leading edge can significantly enhance heat transfer, boost the anti-icing system performance, and greatly enhance flight safety during critical icing weather conditions. Commercially available CFD software, ANSYS Fluent is used to model and analyze the effect of different geometric and flow parameters typical of those found in small to medium category commercial transport aircraft to help determine the optimum arrangement. These parameters include: (1) jet nozzle height-to-slot diameter ratios from 4 to 8, (2) channel width-to-slot diameter ratios from 0.4 to 1.8, and (3) inner-channel inlet location angles from 10° to 60°. Each configuration resulting from a combination of the above parameters was simulated at Reynolds numbers based on jet-slot diameter of 30,000, 60,000, and 90,000. Empirical relations based on available experimental data are used to validate the results. The main findings of the study reveal that the jet height-to-slot diameter ratio of 6, inner channel height-to-slot diameter ratios of 1.8, and inner-channel inlet angular locations of 10° combination resulted in the highest heat transfer at all Reynolds number as well as higher at increased Reynold numbers.

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“…Their results suggested general increases in heat transfer with approximately the 0.7 power of jet Reynolds number. Dyban and Mazur [6] measured heat transfer coefficient on a parabolic concave surface and investigated the effect of jet flow passage curvature. McCormack et al [7] found that Nusselt numbers were increased by 100-150% on the concave surface.…”

Section: Introductionmentioning

confidence: 99%

Computational Analysis of Droplet Mass and Size Effect on Mist/Air Impingement Cooling Performance

et al. 2013

Advances in Mechanical Engineering

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Impingement cooling has been widely employed to cool gas turbine hot components such as combustor liners, combustor transition pieces, turbine vanes, and blades. A promising technology is proposed to enhance impingement cooling with water droplets injection. However, previous studies were conducted on blade shower head film cooling, and less attention was given to the transition piece cooling. As a continuous effort to develop a realistic mist impingement cooling scheme, this paper focuses on simulating mist impingement cooling under typical gas turbine operating conditions of high temperature and pressure in a double chamber model. Furthermore, the paper presents the effect of cooling effectiveness by changing the mass and size of the droplets. Based on the heat-mass transfer analogy, the results of these experiments prove that the mass of 3 − 3 kg/s droplets with diameters of 5-35 m could enhance 90% cooling effectiveness and reduce 122 K of wall temperature. The results of this paper can provide guidance for corresponding experiments and serve as the qualification reference for future more complicated studies with convex surface cooling.

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Heat transfer for a planar air jet striking a concave surface

Cited by 13 publications

References 0 publications

Jet‐Impingement Heat Transfer in Gas Turbine Systems

Jet‐Impingement Heat Transfer in Gas Turbine Systems

Anti-icing hot air jet heat transfer augmentation employing inner channels

Computational Analysis of Droplet Mass and Size Effect on Mist/Air Impingement Cooling Performance

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