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Artículos de revistas sobre el tema "Cooling flow"

Autor: Grafiati

Publicado: 4 de junio de 2021

Última modificación: 1 de febrero de 2022

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1

Zulfikar, Zulfikar. "Penambahan Water Coolant Pada Cooling Tower Tipe Counter Flow." Jurnal Mesin Nusantara 1, no. 2 (2019): 85–92. http://dx.doi.org/10.29407/jmn.v1i2.13566.

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Cooling tower adalah alat penukar kalor dengan fluida kerja air dan udara yang berfungsi mendinginkan air dengan kontak langsung dengan udara yang mengakibatkan sebagian kecil air menguap. Dalam kebanyakan cooling tower yang bekerja pada sistem pendinginan udara menggunakan pompa sentrifugal untuk menggerakkan air vertikal ke atas melintasi menara. Semua cooling tower yang bekerja akan melepaskan kalor melalui kondensor, refrigeran akan melepas kalornya kepada cooling tower sehingga air menjadi panas. Selanjutnya air panas ini akan dipompakan ke cooling tower. Dalam Penelitian ini peneliti aka

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2

Friedrichs, S., H. P. Hodson, and W. N. Dawes. "The Design of an Improved Endwall Film-Cooling Configuration." Journal of Turbomachinery 121, no. 4 (1999): 772–80. http://dx.doi.org/10.1115/1.2836731.

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The endwall film-cooling cooling configuration investigated by Friedrichs et al. (1996, 1997) had in principle sufficient cooling flow for the endwall, but in practice, the redistribution of this coolant by secondary flows left large endwall areas uncooled. This paper describes the attempt to improve upon this datum cooling configuration by redistributing the available coolant to provide a better coolant coverage on the endwall surface, while keeping the associated aerodynamic losses small. The design of the new, improved cooling configuration was based on the understanding of endwall film-coo

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3

Scrittore, J. J., K. A. Thole, and S. W. Burd. "Investigation of Velocity Profiles for Effusion Cooling of a Combustor Liner." Journal of Turbomachinery 129, no. 3 (2006): 518–26. http://dx.doi.org/10.1115/1.2720492.

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Effusion cooling of combustor liners for gas turbine engines is quite challenging and necessary to prevent thermal distress of the combustor liner walls. The flow and thermal patterns in the cooling layer are affected by the closely spaced film-cooling holes. It is important to fully document how the film layer behaves with a full-coverage cooling scheme to gain an understanding into surface cooling phenomena. This paper discusses experimental results from a combustor simulator tested in a low-speed wind tunnel. Engine representative, nondimensional coolant flows were tested for a full-coverag

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4

Wilfert, Gu¨nter, and Stefan Wolff. "Influence of Internal Flow on Film Cooling Effectiveness." Journal of Turbomachinery 122, no. 2 (1999): 327–33. http://dx.doi.org/10.1115/1.555449.

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Film cooling experiments were conducted to investigate the effects of internal flow conditions and plenum geometry on the film cooling effectiveness. The film cooling measurements show a strong influence of the coolant inlet conditions on film cooling performance. The present experiments were carried out on a flat plate with a row of cylindrical holes oriented at 30 deg with respect to a constant-velocity external flow, systematically varying the plenum geometry and blowing rates 0.5⩽M⩽1.25. Adiabatic film cooling measurements using the multiple narrow-banded thermochromic liquid crystal techn

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5

Ba, Wei, Xuesong Li, Xiaodong Ren, and Chunwei Gu. "Aero-thermal coupled through-flow method for cooled turbines with new cooling model." Proceedings of the Institution of Mechanical Engineers, Part A: Journal of Power and Energy 232, no. 3 (2017): 254–65. http://dx.doi.org/10.1177/0957650917731629.

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The aero-thermal–coupled phenomenon is significant in modern cooled turbines, and an aero-thermal coupled through-flow method has previously been developed by the authors for considering the influence of heat transfer and coolant mixing in through-flow design. However, the original cooling model is not capable of calculating the distribution of the coolant mass flow rate and pressure loss in complex cooling structures. Therefore, in this paper, a one-dimensional flow calculation for the internal coolant is introduced into the heat transfer calculation to further improve the through-flow coolin

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6

Wang, Chen, Chunhua Wang, and Jingzhou Zhang. "Parametric Studies of Laminated Cooling Configurations: Overall Cooling Effectiveness." International Journal of Aerospace Engineering 2021 (February 10, 2021): 1–15. http://dx.doi.org/10.1155/2021/6656804.

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Combing the advantages of film cooling, impingement cooling, and enhanced cooling by pin fins, laminated cooling is attracting more and more attention. This study investigates the effects of geometric and thermodynamic parameters on overall cooling effectiveness of laminated configuration, and model experiments were carried out to validate the numerical results. It is found that the increases in film cooling hole diameter and pin fin diameter both result in the increase in cooling effectiveness, but the increases in impingement hole diameter, impingement height, and spanwise hole pitch degrade

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7

Burd, S. W., and T. W. Simon. "Turbulence Spectra and Length Scales Measured in Film Coolant Flows Emerging From Discrete Holes." Journal of Turbomachinery 121, no. 3 (1999): 551–57. http://dx.doi.org/10.1115/1.2841350.

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To date, very little attention has been devoted to the scales and turbulence energy spectra of coolant exiting from film cooling holes. Length-scale documentation and spectral measurements have primarily been concerned with the free-stream flow with which the coolant interacts. Documentation of scales and energy decomposition of the coolant flow leads to more complete understanding of this important flow and the mechanisms by which it disperses and mixes with the free stream. CFD modeling of the emerging flow can use these data as verification that flow computations are accurate. To address th

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8

Takeishi, Kenichiro, Yutaka Oda, and Yuta Egawa. "B114 Film Cooling with Swirling Coolant Flow Induced by Internal Impingement Jet Cooling." Proceedings of the Thermal Engineering Conference 2011 (2011): 29–30. http://dx.doi.org/10.1299/jsmeted.2011.29.

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9

Khalatov, А. А., I. I. Borisov, and Y. J. Dashevskyy. "ADVANCED FILM COOLING SCHEMES: EFFECT OF FLOW ACCELERATION." Industrial Heat Engineering 40, no. 1 (2018): 5–11. http://dx.doi.org/10.31472/ihe.1.2018.01.

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Results of the flow acceleration influence on the film cooling are given for a few variants of coolant supply through a slot, cylindrical or shaped holes, and holes in shallow indentations of different shape - craters, trench, semispherical segments. The correlations for film cooling efficiency prediction are presented.

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10

Friedrichs, S., H. P. Hodson, and W. N. Dawes. "Aerodynamic Aspects of Endwall Film-Cooling." Journal of Turbomachinery 119, no. 4 (1997): 786–93. http://dx.doi.org/10.1115/1.2841189.

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This paper describes an investigation of the aerodynamic aspects of endwall film-cooling, in which the flow field downstream of a large-scale low-speed linear turbine cascade has been measured. The integrated losses and locations of secondary flow features with and without endwall film-cooling have been determined for variations of both the coolant supply pressure and injection location. Together with previous measurements of adiabatic film-cooling effectiveness and surface-flow visualization, these results reveal the nature of the interactions between the ejected coolant and the flow in the b

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11

Flin, P., and J. Krywult. "Subclustering in Cooling and Non-cooling Flow Clusters." Symposium - International Astronomical Union 217 (2004): 118–20. http://dx.doi.org/10.1017/s0074180900197268.

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For 20 hot luminous Beppo-SAX galaxy clusters the occurrence of substrucures has been investigated in 2-D optical data, mainly through the application of the wavelet analysis. Our results are compared with others, coming from 3-D optical data, as well as X-rays. In this sample of galaxy clusters a higher percentage of substructure is observed among non-cooling flow clusters than cooling flow clusters.

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12

Burd, S. W., R. W. Kaszeta, and T. W. Simon. "Measurements in Film Cooling Flows: Hole L/D and Turbulence Intensity Effects." Journal of Turbomachinery 120, no. 4 (1998): 791–98. http://dx.doi.org/10.1115/1.2841791.

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Hot-wire anemometry measurements of simulated film cooling are presented to document the influence of the free-stream turbulence intensity and film cooling hole length-to-diameter ratio on mean velocity and on turbulence intensity. Measurements are taken in the zone where the coolant and free-stream flows mix. Flow from one row of film cooling holes with a streamwise injection of 35 deg and no lateral injection and with a coolant-to-free-stream flow velocity ratio of 1.0 is investigated under free-stream turbulence levels of 0.5 and 12 percent. The coolant-to-free-stream density ratio is unity

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13

Aizon, W. Ghopa Wan, and Kenichi Funazaki. "Aero-Thermal Performance of Purge Flow in Turbine Cascade Endwall Cooling." Applied Mechanics and Materials 229-231 (November 2012): 737–41. http://dx.doi.org/10.4028/www.scientific.net/amm.229-231.737.

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The endwall and blade film cooling systems are the typical solution adopted within gas turbines to allow further increase of turbine inlet temperature, avoiding critical material thermal stresses. Due to complex secondary flow field in the blade passage, endwallis more difficult to cool than blade surfaces. In the matter of fact, in endwall film cooling studies, it is necessary to investigate the interaction between coolant air and the secondary flow. In present study, the flow field of high-pressure turbine cascade has been investigated by 5-holes pitot tube to reveal the secondary flows beha

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14

Coat, C. A., and G. D. Lock. "Flow visualisation experiments for turbine film cooling." Aeronautical Journal 108, no. 1086 (2004): 403–9. http://dx.doi.org/10.1017/s000192400000021x.

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Abstract Flow visualisation experiments related to turbine film cooling have been conducted. These investigated the fluid mechanics of coolant ejection using a large-scale, flat-plate model at engine-representative Reynolds numbers in a low-speed tunnel with ambient-temperature mainstream flow. The coolant trajectories were captured using a fine nylon mesh covered with thermochromic liquid crystals, allowing measurement of gas temperature contours in planes perpendicular to the flow. Three injection geometries were assessed: cylindrical holes with stream-wise injection, cylindrical holes with

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15

Lutum, E., and B. V. Johnson. "Influence of the Hole Length-to-Diameter Ratio on Film Cooling With Cylindrical Holes." Journal of Turbomachinery 121, no. 2 (1999): 209–16. http://dx.doi.org/10.1115/1.2841303.

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Film cooling experiments were conducted to investigate the effects of coolant hole length-to-diameter ratio on the film cooling effectiveness. The results from these experiments offer an explanation for the differences between the film cooling results for cylindrical hole injection configurations previously reported by Goldstein et al. (1974), Pedersen et al. (1977), and Sinha et al. (1991). The previously reported injection configurations differed primarily in coolant hole length-to-diameter ratio. The present experiments were conducted with a row of cylindrical holes oriented at 35 deg to a

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16

Quataert, Eliot, and Ramesh Narayan. "The Cooling Flow to Accretion Flow Transition." Astrophysical Journal 528, no. 1 (2000): 236–42. http://dx.doi.org/10.1086/308171.

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17

Zhang, Jian, Qun Zheng, Guoqiang Yue, and Yuting Jiang. "Investigation on flow field and heat transfer characteristics of film cooling with different swirling directions for coolant flow." Proceedings of the Institution of Mechanical Engineers, Part A: Journal of Power and Energy 235, no. 6 (2021): 1394–405. http://dx.doi.org/10.1177/0957650921997633.

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In this paper, a hexagonal prism inlet chamber is used to form a swirling flow for the film cooling, and three kinds of compound angle of film hole ( γ = 10°, 20°, 30°) with clockwise swirling or counterclockwise swirling are used for numerical simulation studies. The influence of different compound angles of film hole and the swirling directions for the film cooling effectiveness are obtained. The results show that the film cooling effectiveness and spanwise cooling coverage range of the clockwise swirling or counterclockwise swirling flow both are low when the compound angle of film hole is

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18

Song, Yan Ming, and Yang Yang. "CFD Investigation on the Flow Structure inside Cooling Roll." Applied Mechanics and Materials 602-605 (August 2014): 172–75. http://dx.doi.org/10.4028/www.scientific.net/amm.602-605.172.

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Cooling roll is a key component in preparation of amorphous alloy ribbon process. The cooling roll rotates at a high speed that causes large centrifugal force on coolant. The reasonable channel structure facilitates the cooling effect and decreases power consumption. Different channel structures in the cooling roll are analyzed in this paper by computer fluid dynamic (CFD) method. The simulation calculated out the pressure distribution and streamline in different channel structure. The simulation results show that flow in case 2 is the optimal in three channel structures. Finally, the structur

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19

Ryspekova, A., Zh Bolatov, and S. Kunakov. "Heat transfer of the uranium sphere in laminar cooling flow." International Journal of Mathematics and Physics 6, no. 1 (2015): 45–47. http://dx.doi.org/10.26577/2218-7987-2015-6-1-45-47.

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20

Ranson, W. W., K. A. Thole, and F. J. Cunha. "Adiabatic Effectiveness Measurements and Predictions of Leakage Flows Along a Blade Endwall." Journal of Turbomachinery 127, no. 3 (2005): 609–18. http://dx.doi.org/10.1115/1.1929809.

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Traditional cooling schemes have been developed to cool turbine blades using high-pressure compressor air that bypasses the combustor. This high-pressure forces cooling air into the hot main gas path through seal slots. While parasitic leakages can provide a cooling benefit, they also represent aerodynamic losses. The results from the combined experimental and computational studies reported in this paper address the cooling benefit from leakage flows that occur along the platform of a first stage turbine blade. A scaled-up, blade geometry with an upstream slot, a mid-passage slot, and a downst

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21

Zhang, Junhong, Zhexuan Xu, Jiewei Lin, Zefeng Lin, Jingchao Wang, and Tianshu Xu. "Thermal Characteristics Investigation of the Internal Combustion Engine Cooling-Combustion System Using Thermal Boundary Dynamic Coupling Method and Experimental Verification." Energies 11, no. 8 (2018): 2127. http://dx.doi.org/10.3390/en11082127.

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The engine cooling system must be able to match up with the stable operating conditions so as to guarantee the engine performance. On the working cycle level, however, the dynamic thermo-state of engines has not been considered in the cooling strategy. Besides, the frequent over-cooling boiling inside the gallery changes the cooling capacity constantly. It is necessary to study the coupling effect caused by the interaction of cooling flow and in-cylinder combustion so as to provide details of the dynamic control of cooling systems. To this end, this study develops a coupled modeling scheme of

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22

Zhang, Bo, Li-Bing Lin, Ji-Quan Li, Na-Ru Zhang, and Hong-Hu Ji. "Effect of forward expansion angle on film cooling characteristics of shaped holes." Open Physics 18, no. 1 (2020): 302–14. http://dx.doi.org/10.1515/phys-2020-0130.

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AbstractAccording to the design requirements of high-temperature combustion chamber, an advanced shaped hole structure was designed for film cooling. Numerical method was applied in this study to investigate the flow and heat transfer characteristics of shaped holes and compared with those of cylindrical holes. The influence of the forward expansion angle of shaped holes on the flow and heat transfer was studied. The results show that compared to cylindrical holes, the diffused structure of shaped holes decreases the momentum of jet flow, improves the adhesion characteristics of the cooling ai

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23

Thomas, Mitra, and Thomas Povey. "Improving turbine endwall cooling uniformity by controlling near-wall secondary flows." Proceedings of the Institution of Mechanical Engineers, Part G: Journal of Aerospace Engineering 231, no. 14 (2016): 2689–705. http://dx.doi.org/10.1177/0954410016673092.

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In this paper, we propose a design philosophy for cooling high-pressure nozzle guide vane endwalls, which exploits the momentum of cooling jets to control vane secondary flows thereby improving endwall cooling uniformity. The impact of coolant-to-mainstream pressure ratio, hole inclination angle, hole diameter, vane potential field, and overall mass flux ratios are considered. Arguments are developed by examining detailed experimental studies conducted in a large-scale low-speed cascade tunnel with engine-realistic combustor geometry and turbulence profiles. Computational fluid dynamics predic

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24

Zuo, Z. J., Si Bi, L. R. Fu, Z. Q. Weng, and S. H. Peng. "Cooling System Design of Ion Nitriding and PCVD Composite Treatment Furnace." Applied Mechanics and Materials 448-453 (October 2013): 3462–66. http://dx.doi.org/10.4028/www.scientific.net/amm.448-453.3462.

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Keywords: ion nitriding furnace cooling system vacuum system Abstract. About fuction of vacuum plasma nitriding furnace cooling system, and its design and calculation of main parts, in particular control of water consumption. The cooling water system have been set into the water flowing through the four heat shield, and gradually take the heat, then the coolant out by outlet pipe. Cooling water flows through layers of insulation to varying degrees of cooling, to ensure that each level of temperature, precise calculation of water flow can only be guaranteed to ensure the maximum water savings a

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25

Bernsdorf, Stefan, Martin G. Rose, and Reza S. Abhari. "Modeling of Film Cooling—Part I: Experimental Study of Flow Structure." Journal of Turbomachinery 128, no. 1 (2005): 141–49. http://dx.doi.org/10.1115/1.2098768.

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This paper, which is Part I of a two part paper, reports on experimental data taken in a steady flow, flat plate wind tunnel at ETH Zürich, while Part II utilizes this data for calibration and validation purpose of a film cooling model embedded in a 3D CFD code. The facility simulates the film cooling row flow field on the pressure side of a turbine blade. Engine representative nondimensionals are achieved, providing a faithful model at larger scale. Heating the freestream air and strongly cooling the coolant gives the required density ratio between coolant and freestream. The three dimensiona

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26

Torbidoni, Leonardo, and J. H. Horlock. "A New Method to Calculate the Coolant Requirements of a High-Temperature Gas Turbine Blade." Journal of Turbomachinery 127, no. 1 (2005): 191–99. http://dx.doi.org/10.1115/1.1811100.

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Earlier papers by the first author have described a computational method of estimating the cooling flow requirements of blade rows in a high-temperature gas turbine, for convective cooling alone and for convective plus film cooling. This method of analysis and computation, when applied to the whole blade chord was compared to a well-known semi-empirical method. In the current paper, a more sophisticated method is developed from the earlier work and is used to calculate the cooling flow required for a nozzle guide vane (the first blade row) of a high-temperature gas turbine, with given inlet ga

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27

Dong, Hai Hong, and Lin Ruan. "Research on the Flow Characteristics of Forced Circulation Evaporative Cooling System of Stator in Turbo-Generator." Advanced Materials Research 516-517 (May 2012): 1618–21. http://dx.doi.org/10.4028/www.scientific.net/amr.516-517.1618.

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The forced circulation evaporative cooling system of stator in turbo-generator is a new cooling system under study, with the advantages of high-security, high efficiency and energy-saving. In this paper, an experiment table of this new cooling system with single hollow conductor was established. The flow characteristics of coolant in hollow conductor were analyzed and discussed by theoretical simulating and experimental researching. The results show that with the volume flow of coolant increasing, the variation tendencies of total flow resistance in hollow conductor and Xe are not monotonic an

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28

Baek, Seung, and Savas Yavuzkurt. "Effects of Flow Oscillations in the Mainstream on Film Cooling." Inventions 3, no. 4 (2018): 73. http://dx.doi.org/10.3390/inventions3040073.

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The objective of this study is to investigate the effects of oscillations in the main flow and the coolant jets on film cooling at various frequencies (0 to 2144 Hz) at low and high average blowing ratios. Numerical simulations are performed using LES Smagorinsky–Lilly turbulence model for calculation of the adiabatic film cooling effectiveness and using the DES Realizable k-epsilon turbulence model for obtaining the Stanton number ratios (St/Sto). Additionally, multi-frequency inlet velocities are applied to the main and coolant flows to explore the effects of multi-frequency unsteady flows a

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29

Park, Jun Su, Dong-Jun Shin, Sung-Hwan Yim, and Sang-Hyun Kim. "Evaluate the Cooling Performance of Transmit/Receive Module Cooling System in Active Electronically Scanned Array Radar." Electronics 10, no. 9 (2021): 1044. http://dx.doi.org/10.3390/electronics10091044.

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The active electronically scanned array (AESA) radar consists of many transmit/receive (T/R) modules and is used to track missiles approaching destroyers and fighters. The performance of the AESA radar depends on the T/R module temperature. The T/R module temperature should be maintained under 80 °C to guarantee the performance of the AESA radar. In order to match the design requirements of the cooling system of the AESA radar, it is necessary to evaluate the cooling performance according to various operation/installation environments. In this study, computational fluid analysis was performed

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30

Gritsch, Michael, Achmed Schulz, and Sigmar Wittig. "Effect of Internal Coolant Crossflow on the Effectiveness of Shaped Film-Cooling Holes." Journal of Turbomachinery 125, no. 3 (2003): 547–54. http://dx.doi.org/10.1115/1.1580523.

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Film-cooling was the subject of numerous studies during the past decades. However, the effect of flow conditions on the entry side of the film-cooling hole on film-cooling performance has surprisingly not received much attention. A stagnant plenum which is widely used in experimental and numerical studies to feed the holes is not necessarily a right means to re-present real engine conditions. For this reason, the present paper reports on an experimental study investigating the effect of a coolant crossflow feeding the holes that is oriented perpendicular to the hot gas flow direction to model

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31

Pu, Jian, Jian-Hua Wang, Wei Song, and Wei-Long Wu. "Exit-shape effect of film holes at pressure side on trailing edge cutback film cooling characteristics." Proceedings of the Institution of Mechanical Engineers, Part A: Journal of Power and Energy 235, no. 6 (2021): 1315–31. http://dx.doi.org/10.1177/09576509211015473.

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Pressure side (PS) cutback structure has been widely employed in modern turbine blade trailing edge (TE) cooling design. However, hot gas flows around lip of TE slot to generate an impingement to cutback, resulting in a rapid decay of film cooling effectiveness and hence thermal damage of entire TE. Proper angled-ejections upstream of TE can suppress the downstream effectiveness-decay. Therefore, in present work, five types of film-holes were designed to discuss the effect of exit-shape of film-hole on TE film cooling characteristics, inlet boundary layer profile, fluid-interactions, discharge

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32

Pang, S. C., M. A. Kalam, H. H. Masjuki, and M. A. Hazrat. "A review on air flow and coolant flow circuit in vehicles’ cooling system." International Journal of Heat and Mass Transfer 55, no. 23-24 (2012): 6295–306. http://dx.doi.org/10.1016/j.ijheatmasstransfer.2012.07.002.

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33

Cabezon, Francisco A., Allan P. Schinckel, Carol S. Stwalley, and Robert M. Stwalley III. "Heat Transfer Properties of Hog Cooling Pad." Transactions of the ASABE 61, no. 5 (2018): 1693–703. http://dx.doi.org/10.13031/trans.12351.

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Abstract. Thermal stress on sows in modern farrowing operations has become a significant issue for the commercial pork industry. Purdue University researchers have developed a simple conductive hog cooling pad that has the potential to effectively alleviate a significant portion of that heat stress. The heat transfer properties of the cooling pad are crucial to the characterization of the pad and the success of the pad in the field. This article presents data collected showing the thermal profile of the cooling pad, the energy transfer of the pad in operation, and the effectiveness of the pad

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34

O'Connell, R. W. "Star Formation in Cooling Flows." Symposium - International Astronomical Union 127 (1987): 167–77. http://dx.doi.org/10.1017/s0074180900185158.

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Star formation, probably with an abnormal initial mass function, represents the most plausible sink for the large amounts of material being accreted by cD galaxies from cooling flows. There are three prominent cases (NGC 1275, PKS 0745-191, and Abell 1795) where cooling flows have apparently induced unusual stellar populations. Recent studies show that about 50% of other accreting cD's have significant ultraviolet excesses. It therefore appears that detectable accretion populations are frequently associated with cooling flows. The questions of the form of the IMF, the fraction of the flow form

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35

Crawford, C. S., K. A. Arnaud, A. C. Fabian, and R. M. Johnstone. "A2597: Another massive cooling flow." Monthly Notices of the Royal Astronomical Society 236, no. 2 (1989): 277–87. http://dx.doi.org/10.1093/mnras/236.2.277.

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36

Dulikravich, George S. "Inverse Design and Active Control Concepts in Strong Unsteady Heat Conduction." Applied Mechanics Reviews 41, no. 6 (1988): 270–77. http://dx.doi.org/10.1115/1.3151899.

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A summary of recent research in the field of inverse design and optimization of coolant flow passages in the internally cooled configurations is presented. The methodology allows design engineers to prescribe desired surface temperature and heat flux distributions and to fix portions of the multiply connected realistically shaped configurations. The shapes of the resulting coolant flow passages can be arbitrarily or circularly shaped with a capability to maintain certain manufacturing geometric constraints. Unsteady cooling of organs and tissues in bioengineering is demonstrated by determining

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37

Che Sidik, Nor Azwadi, and Shahin Salimi. "The Use of Compound Cooling Holes for Film Cooling at the End Wall of Combustor Simulator." Applied Mechanics and Materials 695 (November 2014): 371–75. http://dx.doi.org/10.4028/www.scientific.net/amm.695.371.

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Gas turbine cooling can be classified into two different schemes; internal and external cooling. In internal cooling method, the coolant provided by compressor is forced into the cooling flow circuits inside turbine components. Meanwhile, for the external cooling method, the injected coolant is directly perfused from coolant manifold to save downstream components against hot gases. Furthermore, in the latter coolant scheme, coolant is used to quell the heat transfer from hot gas stream to a component. There are several ways in external cooling. Film cooling is one of the best cooling systems f

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38

Allen, S. W. "The Impact of Cooling Flows in Clusters of Galaxies." Symposium - International Astronomical Union 195 (2000): 199–206. http://dx.doi.org/10.1017/s007418090016293x.

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I discuss the impact of cooling flows on the observable X-ray properties of clusters of galaxies. I show that accounting for the effects of cooling flows and subcluster merger events leads to consistent determinations of the distribution of gravitating matter in clusters from X-ray and gravitational lensing studies. Accounting for the effects of cooling flows significantly reduces the scatter in the LBol/TX relation determined for the hottest, most luminous systems and changes the best-fitting slope of the relation to a value close to LBol ∝ T2X, in agreement with theoretical models. A clear s

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39

Zhang, Jing Jing, Lian Fu Wang, and Xiang Jun Fang. "Research on Aerodynamic Characteristics of Air-Cooled Turbine Blade with Conjugate Heat Transfer Method." Advanced Materials Research 732-733 (August 2013): 270–75. http://dx.doi.org/10.4028/www.scientific.net/amr.732-733.270.

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In order to improve the performance of aero engines, trying to increase the turbine inlet temperature is an important way. But the turbine inlet temperature of modern aero engines can be more than 2000 K, which is far more than what the materials can bear. So advanced cooling technologies should be introduced to solve this problem. Using the conjugate heat transfer method, this paper researched the aerodynamic characteristics of a certain turbine blade with complex cooling structures. Some conclusions can be drawn: the velocity of the air flow and different distributions of coolant flow for tu

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40

Bao, W., J. Qin, and W. X. Zhou. "Heat transfer characteristic modelling and the effect of operating conditions on re-cooled cycle for a scramjet." Aeronautical Journal 115, no. 1164 (2011): 83–90. http://dx.doi.org/10.1017/s0001924000005479.

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Abstract A re-cooled cycle has been proposed for a regeneratively cooled scramjet to reduce the hydrogen fuel flow for cooling. Upon the completion of the first cooling, fuel can be used for secondary cooling by transferring the enthalpy from fuel to work. Fuel heat sink (cooling capacity) is thus repeatedly used and fuel heat sink is indirectly increased. Instead of carrying excess fuel for cooling or seeking for any new coolant, the cooling fuel flow is reduced, and fuel onboard is adequate to satisfy the cooling requirement for the whole hypersonic vehicle. A performance model considering f

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41

Ebenhoch, G., and T. M. Speer. "Simulation of Cooling Systems in Gas Turbines." Journal of Turbomachinery 118, no. 2 (1996): 301–6. http://dx.doi.org/10.1115/1.2836640.

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The design of cooling systems for gas turbine engine blades and vanes calls for efficient simulation programs. The main purpose of the described program is to determine the complete boundary condition at the coolant side to support a temperature calculation for the solid. For the simulation of convection and heat pick up of the coolant flow, pressure loss, and further effects to be found in a rotating frame, the cooling systems are represented by networks of nodes and flow elements. Within each flow element the fluid flow is modeled by a system of ordinary differential equations based on the o

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42

Patil, Mahesh, Satyam Panchal, Namwon Kim, and Moo-Yeon Lee. "Cooling Performance Characteristics of 20 Ah Lithium-Ion Pouch Cell with Cold Plates along Both Surfaces." Energies 11, no. 10 (2018): 2550. http://dx.doi.org/10.3390/en11102550.

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Temperature control of the lithium-ion pouch cells is crucial for smooth operation, longevity and enhanced safety in the battery-operated electric vehicles. Investigating the thermal behavior of lithium-ion pouch cells and optimizing the cooling performance are required to accomplish better performance, long life, and enhanced safety. In the present study, the cooling performance characteristics of 20 Ah lithium-ion pouch cell with cold plates along both surfaces are investigated by varying the inlet coolant mass flow rates and the inlet coolant temperatures. The inlet coolant mass flow rate i

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43

Lenzi, Tommaso, Alessio Picchi, Tommaso Bacci, Antonio Andreini, and Bruno Facchini. "Unsteady Flow Field Characterization of Effusion Cooling Systems with Swirling Main Flow: Comparison Between Cylindrical and Shaped Holes." Energies 13, no. 19 (2020): 4993. http://dx.doi.org/10.3390/en13194993.

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The presence of injectors with strongly swirled flows, used to promote flame stability in the combustion chambers of gas turbines, influences the behaviour of the effusion cooling jets and consequently of the liner’s cooling capabilities. For this reason, unsteady behaviour of the jets in the presence of swirling flow requires a characterization by means of experimental flow field analyses. The experimental setup of this work consists of a non-reactive single-sector linear combustor test rig, scaled up with respect to the real engine geometry to increase spatial resolution and to reduce the fr

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44

McLean, Christopher, Cengiz Camci, and Boris Glezer. "Mainstream Aerodynamic Effects Due to Wheelspace Coolant Injection in a High-Pressure Turbine Stage: Part II—Aerodynamic Measurements in the Rotational Frame." Journal of Turbomachinery 123, no. 4 (2001): 697–703. http://dx.doi.org/10.1115/1.1397303.

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The current paper deals with the aerodynamic measurements in the rotational frame of reference of the Axial Flow Turbine Research Facility (AFTRF) at the Pennsylvania State University. Stationary frame measurements of “Mainstream Aerodynamic Effects Due to Wheelspace Coolant Injection in a High Pressure Turbine Stage” were presented in Part I of this paper. The relative aerodynamic effects associated with rotor–nozzle guide vane (NGV) gap coolant injections were investigated in the rotating frame. Three-dimensional velocity vectors including exit flow angles were measured at the rotor exit. Th

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45

Nulsen, PEJ. "Star Formation in Cooling Flows." Australian Journal of Physics 45, no. 4 (1992): 501. http://dx.doi.org/10.1071/ph920501.

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There is good evidence that the intracluster gas near the centres of many clusters of galaxies is cooling over at least a decade in temperature. This results in an inflow, which is approximately steady where the cooling time of the gas is shorter than the age of the flow. X-ray observations indicate that the cooling gas must have substantial inhomogeneities. Non-linear development of thermal instability causes cooled gas clouds to be deposited throughout the region of the steady cooling flow. The masses of these clouds will be small, typically a lot less than a Jeans mass when they first form.

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46

Kohli, A., and D. G. Bogard. "Fluctuating Thermal Field in the Near-Hole Region for Film Cooling Flows." Journal of Turbomachinery 120, no. 1 (1998): 86–91. http://dx.doi.org/10.1115/1.2841393.

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The film cooling flow field is the result of a highly complex interaction between the film cooling jets and the mainstream. Understanding this interaction is important in order to explain the physical mechanisms involved in the rapid decrease of effectiveness, which occurs close to the hole exit. Not surprisingly, it is this region that is not modeled satisfactorily with current film cooling models. This study uses a high-frequency-response temperature sensor, which provides new information about the film cooling flow in terms of actual turbulence levels and probability density functions of th

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47

Takeishi, Kenichiro, Masaharu Komiyama, Yutaka Oda, and Yuta Egawa. "Aerothermal Investigations on Mixing Flow Field of Film Cooling With Swirling Coolant Flow." Journal of Turbomachinery 136, no. 5 (2013). http://dx.doi.org/10.1115/1.4023909.

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This paper describes the experimental results of a new film cooling method that utilizes swirling coolant flow through circular and shaped film cooling holes. The experiments were conducted by using a scale-up model of a film-cooling hole installed on the bottom surface of a low-speed wind tunnel. Swirling motion of the film coolant was induced inside a hexagonal plenum using two diagonal impingement jets, which were inclined at an angle of α toward the vertical direction and installed in staggered positions. These two impingement jets generated a swirling flow inside the plenum, which entered

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48

Alqefl, Mahmood H., Kedar P. Nawathe, Pingting Chen, Rui Zhu, Yong W. Kim, and Terrence W. Simon. "Effects of Endwall Film Coolant Flowrate on Secondary Flows and Coolant Mixing in a First Stage Nozzle Guide Vane." Journal of Turbomachinery 143, no. 3 (2021). http://dx.doi.org/10.1115/1.4049852.

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Abstract Modern gas turbines are subjected to very high thermal loading. This leads to a need for aggressive cooling to protect components from damage. Endwalls are particularly challenging to cool due to a complex system of secondary flows near them that wash and disrupt the protective coolant films. This highly three-dimensional flow not only affects but is also affected by the momentum of film cooling flows, whether injected just upstream of the passage to intentionally cool the endwall or as combustor cooling flows injected further upstream in the engine. This complex interaction between t

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49

Alqefl, Mahmood H., Kedar P. Nawathe, Pingting Chen, Rui Zhu, Yong W. Kim, and Terrence W. Simon. "Aero-Thermal Aspects of Film Cooled Nozzle Guide Vane Endwall—Part 2: Thermal Measurements." Journal of Turbomachinery 143, no. 12 (2021). http://dx.doi.org/10.1115/1.4051556.

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Abstract Flow over gas turbine endwalls is complex and highly three-dimensional. As boundaries for modern engine designs are pushed, this already-complex flow is affected by aggressive application of film cooling flows that actively interact. This two-part study describes, experimentally, the aero-thermal interaction of cooling flows near the endwall of a first-stage nozzle guide vane passage (NGV). The approach flow conditions represent flow exiting a low-NOx combustor. The test section includes geometric and cooling details of a combustor-turbine interface in addition to endwall film cooling

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50

Fraas, Marc, Tobias Glasenapp, Achmed Schulz, and Hans-Jörg Bauer. "Film Cooling Measurements for a Laidback Fan-Shaped Hole: Effect of Coolant Crossflow on Cooling Effectiveness and Heat Transfer." Journal of Turbomachinery 141, no. 4 (2019). http://dx.doi.org/10.1115/1.4041655.

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Internal coolant passages of gas turbine vanes and blades have various orientations relative to the external hot gas flow. As a consequence, the inflow of film cooling holes varies as well. To further identify the influencing parameters of film cooling under varying inflow conditions, the present paper provides detailed experimental data. The generic study is performed in a novel test rig, which enables compliance with all relevant similarity parameters including density ratio. Film cooling effectiveness as well as heat transfer of a 10–10–10 deg laidback fan-shaped cooling hole is discussed.

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