Experimental and Numerical Study of 3D Printed Direct Jet Impingement Cooling for High Power, Large Die Size Applications

2020 ◽  
pp. 1-1
Author(s):  
T.-W. Wei ◽  
H. Oprins ◽  
V. Cherman ◽  
Z. Yang ◽  
K. Rivera ◽  
...  
Keyword(s):  
High Power ◽  
Numerical Study ◽  
Jet Impingement ◽  
Impingement Cooling ◽  
3D Printed

Experimental and Numerical Study of Array Jet Impingement Cooling on a Leading Edge Curved Surface

2021 ◽  
Author(s):  
Husam Zawati ◽  
Jorge Torres ◽  
Erik Fernandez ◽  
Jose Rodriguez ◽  
Jayanta Kapat
Keyword(s):  
Numerical Study ◽  
Leading Edge ◽  
Jet Impingement ◽  
Curved Surface ◽  
Impingement Cooling

Numerical Study on Flow and Heat Transfer Characteristics of Jet Impingement Cooling

2011 ◽  
Vol 148-149 ◽  
pp. 680-683
Author(s):  
Run Peng Sun ◽  
Wei Bing Zhu ◽  
Hong Chen ◽  
Chang Jiang Chen
Keyword(s):  
Heat Transfer ◽  
Reynolds Number ◽  
Numerical Study ◽  
Cross Flow ◽  
Jet Impingement ◽  
Local Heat Transfer ◽  
Transfer Characteristic ◽  
Heat Transfer Characteristics ◽  
Impingement Cooling ◽  
Transfer Characteristics

Three-dimensional numerical study is conducted to investigate the heat transfer characteristics for the flow impingement cooling in the narrow passage based on cooling technology of turbine blade.The effects of the jet Reynolds number, impingement distance and initial cross-flow on heat transfer characteristic are investigated.Results show that when other parameters remain unchanged local heat transfer coefficient increases with increase of jet Reynolds number；overall heat transfer effect is reduced by initial cross-flow；there is an optimal distance to the best effect of heat transfer.

scholarly journals Micro scale jet impingement cooling and its efficacy on turbine vanes : a numerical study

2021 ◽  
Author(s):  
Santhiya Jayaraman
Keyword(s):  
Heat Transfer ◽  
Numerical Study ◽  
Leading Edge ◽  
Jet Impingement ◽  
3D Analysis ◽  
Transfer Rates ◽  
Impingement Cooling ◽  
Micro Scale ◽  
Turbine Vane ◽  
Nozzle Configuration

A numerical analysis of effectiveness of micro-jet impingement cooling on leading edge of a turbine vane is presented. An axisymmetric single round jet was assessed for its ability and consistency as a preliminary study including the investigation of parameters influencing the heat transfer distribution. The analysis revealed that an increase in Nusselt number was attributed to increase in Reynolds number, decrease in jet diameter and H/D < 3. Significant improvement in heat transfer was observed for tapering nozzle configuration. The study was then further expanded to 3D analysis of leading edge cooling of turbine vane. Effect of nozzle diameter to micro-scale was studied, which showed 65% enhancement in the heat transfer rates.

Experimental and Numerical Study of Jet Impingement Cooling for Improved Gas Turbine Blade Internal Cooling With In-Line and Staggered Nozzle Arrays

2020 ◽  
Vol 143 (1) ◽  
Author(s):  
Abdel Rahman Salem ◽  
Farah Nazifa Nourin ◽  
Mohammed Abousabae ◽  
Ryoichi S. Amano
Keyword(s):  
Heat Transfer ◽  
Nusselt Number ◽  
Gas Turbine ◽  
Numerical Study ◽  
Turbine Blades ◽  
Jet Impingement ◽  
Target Surface ◽  
Internal Cooling ◽  
Impingement Cooling ◽  
Gas Turbine Blades

Abstract Internal cooling of gas turbine blades is performed with the combination of impingement cooling and serpentine channels. Besides gas turbine blades, the other turbine components such as turbine guide vanes, rotor disks, and combustor wall can be cooled using jet impingement cooling. This study is focused on jet impingement cooling, in order to optimize the coolant flow, and provide the maximum amount of cooling using the minimum amount of coolant. The study compares between different nozzle configurations (in-line and staggered), two different Reynold's numbers (1500 and 2000), and different stand-off distances (Z/D) both experimentally and numerically. The Z/D considered are 3, 5, and 8. In jet impingement cooling, the jet of fluid strikes perpendicular to the target surface to be cooled with high velocity to dissipate the heat. The target surface is heated up by a direct current (DC) power source. The experimental results are obtained by means of thermal image processing of the captured infra-red (IR) thermal images of the target surface. Computational fluid dynamics (CFD) analysis were employed to predict the complex heat transfer and flow phenomena, primarily the line-averaged and area-averaged Nusselt number and the cross-flow effects. In the current investigation, the flow is confined along with the nozzle plate and two parallel surfaces forming a bi-directional channel (bi-directional exit). The results show a comparison between heat transfer enhancement with in-line and staggered nozzle arrays. It is observed that the peaks of the line-averaged Nusselt number (Nu) become less as the stand-off distance (Z/D) increases. It is also observed that the fluctuations in the stagnation heat transfer are caused by the impingement of the primary vortices originating from the jet nozzle exit.

Numerical Study of Flow and Heat Transfer of Impingement Cooling on Model of Turbine Blade Leading Edge

2010 ◽  
Author(s):  
Zhao Liu ◽  
Zhenping Feng ◽  
Liming Song
Keyword(s):  
Heat Transfer ◽  
Turbine Blade ◽  
Numerical Study ◽  
Leading Edge ◽  
Jet Impingement ◽  
Target Surface ◽  
Nozzle Diameter ◽  
Impingement Cooling ◽  
Jet Nozzle ◽  
Blade Leading Edge

In this paper a numerical simulation is performed to simulate the impingement cooling on internal leading edge region, which is stretched by the middle cross section of the first stage rotor blade of GE-E3 engine high pressure turbine, and in the condition that jets flow is ejected from a row of four different diameter circular nozzles. The relative performances of three versions of turbulence models including the RNG κ-ε model, the standard κ-ω model and the SST κ-ω model in the simulation of a row of circle jet impingement heat transfer are compared with available experimental data. The results show that SST κ-ω model is the best one based on simulation accuracy. Then the SST κ-ω model is adopted for the simulation. The grid independence study is also carried out by using the Richardson extrapolation method. A single array of circle jets is arranged to investigate the impingement cooling and its effectiveness. Four different jet nozzle diameters are studied and seven different inlet flow Mach numbers of each jet nozzle diameter are calculated. The influence of the ratio of the spacing of jet nozzle from the target surface to the jet nozzle diameter on impingement cooling is also studied, in case of a constant ratio of jet spacing to jet nozzle diameter in different jet nozzle diameters. The results indicate that the heat transfer coefficient on the turbine blade leading edge increases with the increase of jet Mach number and jet nozzle diameter, the spanwise area weight average Nusselt number decreases with the increase of the ratio of the spacing of jet nozzle from the target surface to jet nozzle diameter, and a lower ratio of spacing of jet nozzle from the target surface to the jet nozzle diameter is desirable to improve the performance of impingement cooling on turbine leading edge.

Experimental/Numerical Study of Multiple Rows of Confined Jet Impingement Normal to a Surface at Close Distances

2012 ◽  
Author(s):  
M. E. Taslim ◽  
N. Rosso
Keyword(s):  
Heat Transfer ◽  
Gas Turbine ◽  
Numerical Study ◽  
Turbulence Models ◽  
Jet Impingement ◽  
Hole Diameter ◽  
Impingement Cooling ◽  
Discharge Coefficients ◽  
Hexahedral Elements ◽  
D Values

Impingement cooling is used in a variety of applications ranging from industrial bakeries, paper processing, heat exchangers and specially gas turbine engines of all sizes to name a few. Convective impingement cooling has been studied numerous times in a variety of configurations. However little work has been conducted regarding impingement between two surfaces separated by less than one impingement jet hole diameter. This configuration is of special interest for gas turbine cooling applications such as in shrouds, combustor liners and airfoils cooling cavities where small holes are used to cool and purge cavities between two adjacent pieces of hardware. In this study, flow and temperature fields as well as heat transfer coefficients for confined jet impingement are being investigated for multiple rows of round jets impinging normal to a target surface less than one hole diameter from the jet origin. The experiments were conducted for five rows of jets with five jets on each row and steady-state liquid crystal thermography for heat transfer measurements were utilized. Numerical results were obtained from a three-dimensional unstructured computational fluid dynamics model with over 4 million hexahedral elements. For turbulence modeling, the realizable k–ε was employed in combination with enhanced wall treatment approach for the near wall regions. Other available RANS turbulence models such as k–ω, v2f and large eddy simulation were tried for selected geometries and results are compared with those of k–ε model. Nusselt numbers on the target areas and discharge coefficients for flow across the jet holes are reported for jet Reynolds numbers ranging from 10000 to 50000, pitch-to-diameter, P/d, values of 2,3 and 4, each for jet distance-to-diameter Z/d, values of 0.3, 0.4, 0.5, 0.6, 0.8, 1, 2 and 3. Comparisons are made between the test and numerically-obtained results in order to evaluate the employed turbulence models and validate the numerically obtained results. Results showed severe reduction in discharge coefficients as the jet holes were brought closer to each other and closer to the target wall. Heat transfer performance for the hole lateral spacing of P/d = 4 was found to be superior to that for P/d = 2 or P/d = 3.

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