Relevant bibliographies by topics / Film cooling

Contents

  1. Journal articles
  2. Dissertations / Theses
  3. Books
  4. Book chapters
  5. Conference papers
  6. Reports

Academic literature on the topic 'Film cooling'

Author: Grafiati
Published: 4 June 2021
Last updated: 26 July 2025

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Journal articles on the topic "Film cooling"

1

Shi, Li, Zhiying Sun, and Yuanfeng Lu. "The Combined Influences of Film Cooling and Thermal Barrier Coatings on the Cooling Performances of a Film and Internal Cooled Vane." Coatings 10, no. 9 (2020): 861. http://dx.doi.org/10.3390/coatings10090861.

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This paper presents a numerical investigation on the combined influences of film cooling and thermal barrier coatings (TBCs) on the cooling performances of a NASA C3X guide vane. The results show that: (1) film cooling on the pressure side is more effective than suction side, especially on the trailing edge where multiple cooling and thermal protection techniques include internal cooling and TBCs are necessary. (2) TBCs show positive and negative roles in improving cooling performance at the same time for the coated vane with or without film cooling. Without film cooling, TBCs show negative ro
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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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Shangguan, Yanqin, and Fei Cao. "The Evolution of Flow Structures and Coolant Coverage in Double-Row Film Cooling with Upstream Forward Jets and Downstream Backward Jets." Energies 17, no. 14 (2024): 3387. http://dx.doi.org/10.3390/en17143387.

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The spatiotemporal evolution of the flow structures and coolant coverage of double-row film cooling with upstream forward jets and downstream backward jets, having a significant impact on film-cooling performance, is studied using the simplified thermal lattice Boltzmann method (STLBM). Moreover, the effect of the inclination angle of downstream backward jets is considered. The high-performance simulations of film cooling have been conducted by using our verified in-house solver. Results show that special flow structures, such as a sand dune-shaped protrusion, appear in double-row film cooling
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Harrington, Mark K., Marcus A. McWaters, David G. Bogard, Christopher A. Lemmon, and Karen A. Thole. "Full-Coverage Film Cooling With Short Normal Injection Holes." Journal of Turbomachinery 123, no. 4 (2001): 798–805. http://dx.doi.org/10.1115/1.1400111.

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An experimental and computational investigation was conducted on the film cooling adiabatic effectiveness of a flat plate with full coverage film cooling. The full coverage film cooling array was comprised of ten rows of coolant holes, arranged in a staggered pattern, with short L/D=1, normal coolant holes. A single row of cooland holes was also examined to determine the accuracy of a superposition prediction of the full coverage adiabatic effectiveness performance. Large density coolant jets and high mainstream turbulence conditions were utilized to simulate realistic engine conditions. High-
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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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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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Wang, J. H., J. Messner, and H. Stetter. "An Experimental Investigation on Transpiration Cooling Part II: Comparison of Cooling Methods and Media." International Journal of Rotating Machinery 10, no. 5 (2004): 355–63. http://dx.doi.org/10.1155/s1023621x04000363.

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This article attempts to provide a cooling performance comparison of various mass transfer cooling methods and different cooling media through two experiments. In the first experiment, pressurized air was used as a cooling medium and two different circular tubes were used as specimens. One is made of impermeable solid material with four rows of discrete holes to simulate film cooling, and the other consists of sintered porous material to create a porous transpiration cooling effect. The natures of transpiration cooling and film cooling including leading and trailing edge injection cooling were
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Vasu Devan Nair Girija Kumari, Krishna Anand, and Parammasivam Kanjikoil Mahali. "Investigations of improved cooling effectiveness for ramp film cooling with compound angle film cooling jets." Aircraft Engineering and Aerospace Technology 93, no. 6 (2021): 971–84. http://dx.doi.org/10.1108/aeat-05-2020-0082.

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Purpose This paper aims to investigate the film cooling effectiveness (FCE) and mixing flow characteristics of the flat surface ramp model integrated with a compound angled film cooling jet. Design/methodology/approach Three-dimensional numerical simulation is performed on a flat surface ramp model with Reynolds Averaged Navier-Stokes approach using a finite volume solver. The tested model has a fixed ramp angle of 24° and a ramp width of two times the diameter of the film cooling hole. The coolant air is injected at 30° along the freestream direction. Three different film hole compound angles
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Bazdidi-Tehrani, F., and G. E. Andrews. "Full-Coverage Discrete Hole Film Cooling: Investigation of the Effect of Variable Density Ratio." Journal of Engineering for Gas Turbines and Power 116, no. 3 (1994): 587–96. http://dx.doi.org/10.1115/1.2906860.

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Experimental results of the overall and adiabatic cooling effectiveness for full-coverage discrete hole film cooling are presented for a range of practical geometries. The results are reported for various hot gas mainstream-to-coolant temperature (density) ratios, in the realistic range of 1.0–3.2. The variation of this ratio was achieved by increasing the crossflow mainstream temperature, over the range 300–930 K. For combustor wall film cooling applications, the overall cooling effectiveness increased significantly with the number of holes per unit wall surface area, over the range of 4306–2
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Shangguan, Yanqin, and Fei Cao. "An LBM-Based Investigation on the Mixing Mechanism of Double Rows Film Cooling with the Combination of Forward and Backward Jets." Energies 15, no. 13 (2022): 4848. http://dx.doi.org/10.3390/en15134848.

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Film cooling has been widely applied to the highly efficient thermal protection of gas turbines. By using the simplified thermal lattice Boltzmann method (STLBM), a series of large-scale simulations of film cooling are performed to dig up the mixing mechanism of double rows film cooling with the combination of forward and backward jets at the first attempt. The combination of an upstream row with forward jet and a downstream row with backward jet is considered. The Reynolds number is 4000. The blowing ratio of the upstream coolant jet is fixed as BR1=0.5. For the downstream coolant jet (BR2),
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Dissertations / Theses on the topic "Film cooling"

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Hossain, Mohammad Arif. "Sweeping Jet Film Cooling." The Ohio State University, 2020. http://rave.ohiolink.edu/etdc/view?acc_num=osu1586462423029754.

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Strater, Kurt F. "Countercurrent cooling of blown film." Thesis, McGill University, 1985. http://digitool.Library.McGill.CA:80/R/?func=dbin-jump-full&object_id=66003.

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Fawcett, Richard James. "Coherent unsteadiness in film cooling." Thesis, University of Oxford, 2011. http://ora.ox.ac.uk/objects/uuid:57ec3da6-4946-4f66-8421-b01d53d7e0fc.

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Film cooling is vital for the cooling of the blades and vanes in the high temperature environment of a jet engine high pressure turbine stage. Previous research into film cooling has typically concentrated on its time-mean performance. However, results from other studies upon more simplified geometries, suggest that coherent unsteadiness is likely to also be present in film cooling flows. The research presented in this thesis, therefore, aims to characterise what coherent unsteadiness, if any, is present within film cooling flows. Cylindrical and shaped cooling holes, located upon the pressure
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Aghasi, Paul P. "Dependence of Film Cooling Effectiveness on 3D Printed Cooling Holes." University of Cincinnati / OhioLINK, 2016. http://rave.ohiolink.edu/etdc/view?acc_num=ucin1458893416.

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Nowlin, Scott Raymond. "The use of intersecting film cooling passages for nozzle guide vane cooling." Thesis, University of Oxford, 2009. http://ethos.bl.uk/OrderDetails.do?uin=uk.bl.ethos.670018.

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Licu, Dragos N. "Heat transfer characteristics in film cooling applications." Thesis, National Library of Canada = Bibliothèque nationale du Canada, 1998. http://www.collectionscanada.ca/obj/s4/f2/dsk2/tape17/PQDD_0005/NQ34581.pdf.

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Friedrichs, Stefan. "Endwall film-cooling in axial flow turbines." Thesis, University of Cambridge, 1997. http://ethos.bl.uk/OrderDetails.do?uin=uk.bl.ethos.627225.

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Telisinghe, Janendra C. "Film cooling of turbine blade trailing edges." Thesis, University of Oxford, 2013. http://ora.ox.ac.uk/objects/uuid:86c06246-16e9-4378-9a61-e09317d31a92.

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In modern gas turbine engines, film cooling is extensively used to cool the components exposed to the hot mainstream gas path. In implementing film cooling on modern gas turbine engines, the trailing edge film poses a particularly challenging design problem. From an aerodynamic point of view, the trailing edge of a blade is designed to be as thin as possible. However, this conflicts with the implementation of the cooling design. The most common method of film cooling the trailing edge is via late pressure surface discrete film cooling holes. Another method of cooling the trailing edge is by us
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Renze, Peter Clemens-August. "Large eddy simulation of film cooling flows /." Aachen : Shaker, 2008. http://d-nb.info/989959031/04.

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Kheniser, Issam E. "Film Cooling Experiments in a Medium Duration Blowdown Facility." The Ohio State University, 2010. http://rave.ohiolink.edu/etdc/view?acc_num=osu1276540410.

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Books on the topic "Film cooling"

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Aerssens, S. E. E. Modelling of two-dimensional film cooling. UMIST, 1994.

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Simon, Frederick F. Jet model for slot film cooling with effect of free-stream and coolant turbulence. Lewis Research Center, 1986.

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Nan-Suey, Liu, and NASA Glenn Research Center, eds. Film cooling flow effects on post-combustor trace chemistry. National Aeronautics and Space Administration, Glenn Research Center, 2003.

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Garg, Vijay Kumar. Effect of coolant temperature and mass flow on film cooling of turbine blades. National Aeronautics and Space Administration, 1997.

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Olsen, George C. Hydrogen film cooling with incident and swept-shock interactions in a Mach 6.4 nitrogen free stream. Langley Research Center, 1995.

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Acharya, Sumanta. Large eddy simulations and turbulence modeling for film cooling. National Aeronautics and Space Administration, Glenn Research Center, 1999.

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Ward, S. C. Validation of a CFD model for predicting film cooling performance. American Institute of Aeronautics and Astronautics, 1993.

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Garg, Vijay Kumar. Leading edge film cooling effects on turbine blade heat transfer. National Aeronautics and Space Administration, 1995.

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Lepicovsky, J. Application of thin-film thermocouples to localized heat transfer measurements. National Aeronautics and Space Administration, 1995.

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J, Bruckner R., Smith F. A, and United States. National Aeronautics and Space Administration., eds. Application of thin-film thermocouples to localized heat transfer measurements. National Aeronautics and Space Administration, 1995.

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Book chapters on the topic "Film cooling"

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Bogard, David G., and Karen A. Thole. "Film Cooling." In Turbine Aerodynamics, Heat Transfer, Materials, and Mechanics. American Institute of Aeronautics and Astronautics, Inc., 2014. http://dx.doi.org/10.2514/5.9781624102660.0223.0274.

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Herwig, Heinz. "Filmkühlung (film cooling)." In Wärmeübertragung A-Z. Springer Berlin Heidelberg, 2000. http://dx.doi.org/10.1007/978-3-642-56940-1_14.

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Peter, Johannes M. F., and Markus J. Kloker. "Numerical Simulation of Film Cooling in Supersonic Flow." In Notes on Numerical Fluid Mechanics and Multidisciplinary Design. Springer International Publishing, 2020. http://dx.doi.org/10.1007/978-3-030-53847-7_5.

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Abstract High-order direct numerical simulations of film cooling by tangentially blowing cool helium at supersonic speeds into a hot turbulent boundary-layer flow of steam (gaseous H2O) at a free stream Mach number of 3.3 are presented. The stagnation temperature of the hot gas is much larger than that of the coolant flow, which is injected from a vertical slot of height s in a backward-facing step. The influence of the coolant mass flow rate is investigated by varying the blowing ratio F or the injection height s at kept cooling-gas temperature and Mach number. A variation of the coolant Mach
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Ludescher, Sandra, and Herbert Olivier. "Film Cooling in Rocket Nozzles." In Notes on Numerical Fluid Mechanics and Multidisciplinary Design. Springer International Publishing, 2020. http://dx.doi.org/10.1007/978-3-030-53847-7_4.

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Abstract In this project supersonic, tangential film cooling in the expansion part of a nozzle with rocket-engine like hot gas conditions was investigated. Therefore, a parametric study in a conical nozzle was conducted revealing the most important influencing parameter on film cooling for the presented setup. Additionally, a new axisymmetric film cooling model and a method for calculating the cooling efficiency from experimental data was developed. These models lead to a satisfying correlation of the data. Furthermore, film cooling in a dual-bell nozzle performing in altitude mode was investi
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Guo, Tingting, Shaohua Li, and Jianhong Liu. "Large Eddy Simulation of Film Cooling." In Challenges of Power Engineering and Environment. Springer Berlin Heidelberg, 2007. http://dx.doi.org/10.1007/978-3-540-76694-0_267.

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Krishna, Anand V. G. "Investigations on improved trenched cooling effectiveness with modified film cooling holes." In Challenges and Opportunities in Industrial and Mechanical Engineering: A Progressive Research Outlook. CRC Press, 2024. http://dx.doi.org/10.1201/9781032713229-112.

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Suresh, Batchu, Resham D. Khade, V. Kesavan, and D. Kishore Prasad. "Investigation for the Improvement of Film Cooling Effectiveness of Effusion Cooling Holes." In Proceedings of the National Aerospace Propulsion Conference. Springer Singapore, 2020. http://dx.doi.org/10.1007/978-981-15-5039-3_10.

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Kulju, Timo, Juha Pyykkönen, David C. Martin, Esa Muurinen, and Riitta L. Keiski. "CFD-Simulation of Film Boiling at Steel Cooling Process." In Film and Nucleate Boiling Processes. ASTM International, 2011. http://dx.doi.org/10.1520/stp49331t.

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Kulju, Timo, Juha Pyykkönen, David C. Martin, Esa Muurinen, and Riitta L. Keiski. "CFD-Simulation of Film Boiling at Steel Cooling Process." In Film and Nucleate Boiling Processes. ASTM International, 2011. http://dx.doi.org/10.1520/stp153420120002.

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Medic, Gorazd, and Paul Durbin. "RANS Simulations for Film-Cooling Analysis and Design." In Modelling Fluid Flow. Springer Berlin Heidelberg, 2004. http://dx.doi.org/10.1007/978-3-662-08797-8_15.

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Conference papers on the topic "Film cooling"

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Mortensen, Kenneth P., and Stephen N. Conley. "Film Fill Fouling in Counterflow Cooling Towers: Research Results." In CORROSION 1994. NACE International, 1994. https://doi.org/10.5006/c1994-94457.

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Abstract High-efficiency cross-corrugated PVC film packing materials, first Introduced In the U.S. for new counterflow cooling tower products In the 1970’s, have In a number of Instances recently been used to Improve the thermal performance of older splash and flat-sheet-filled counterflow towers. These highly interfaced PVC packs In new tower and retrofit service have been applied In a variety of circumstances and conditions. In some locations raw waters have fouled packs. This fouling process can, if left unchecked, reverse performance gains from the tower upgrade and add substantially to co
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Takeishi, K., Y. Oda, Y. Egawa, and T. Kitamura. "Film cooling with swirling coolant flow." In HEAT TRANSFER 2010. WIT Press, 2010. http://dx.doi.org/10.2495/ht100171.

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Yusop, Nadiahnor Md, Gordon E. Andrews, Derek B. Ingham, I. M. Khalifa, Mike C. Mkpadi, and Mohammed Pourkashanian. "Predictions of Adiabatic Film Cooling Effectiveness for Effusion Film Cooling." In ASME Turbo Expo 2007: Power for Land, Sea, and Air. ASMEDC, 2007. http://dx.doi.org/10.1115/gt2007-27467.

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This paper presents computational predictions of adiabatic film cooling effectiveness for effusion cooling systems with 90° and 30° holes. Predictions are performed for a range of coolant injection mass flow rates per unit surface area, G, of 0.1kg/sm2 - 1.6 kg/sm2 for 90° holes with constant pitch-to-diameter ratio of X/D = 11 and 10 rows of holes and for 30° inclined holes with X/D = 11 and 15 rows of holes over a 152mm surface length. The computational works performed are steady-state and the turbulent governing equations are solved by a control-volume-based finite difference method with se
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BASS, ROBERT, LARRY HARDIN, RICHARD RODGERS, and RICHARD ERNST. "Supersonic film cooling." In 2nd International Aerospace Planes Conference. American Institute of Aeronautics and Astronautics, 1990. http://dx.doi.org/10.2514/6.1990-5239.

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Bai, Jiang-Tao, Hui-ren Zhu, and Cun-liang Liu. "Film Cooling Characteristic of Double-Fan-Shaped Film Cooling Holes." In ASME Turbo Expo 2009: Power for Land, Sea, and Air. ASMEDC, 2009. http://dx.doi.org/10.1115/gt2009-59318.

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The film cooling performance downstream of a single row of double-fan-shaped film cooling holes in a flat plate have been investigated by experimental measurements and numerical simulation. The entrance and exit of double-fan-shaped holes are comprised of a lateral expansion of 15° from the original simple cylindrical shape with stream-wise inclination of 45°. The width of the exit face to cylinder diameter ratio is 1.5; the length-to-diameter ratio is 4.24 and the pitch-to-diameter ratio is 3. The experimental method used to obtain the adiabatic film cooling effectiveness values and the heat
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Natsui, Greg, Zachary Little, Jay Kapat, Anthony Socotch, Anquan Wang, and Jason E. Dees. "Adiabatic Film Cooling Effectiveness Measurements Throughout Multi-Row Film Cooling Arrays." In ASME Turbo Expo 2016: Turbomachinery Technical Conference and Exposition. American Society of Mechanical Engineers, 2016. http://dx.doi.org/10.1115/gt2016-56183.

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Adiabatic film cooling effectiveness measurements are obtained using pressure-sensitive paint (PSP) on a flat film cooled surface. The effects of blowing ratio and hole spacing are investigated for four multi-row arrays comprised of 8 rows containing 52 holes of 3.8 mm diameter with 20° inclination angles and hole length-to-diameter ratio of 11.2. The four arrays investigated have two different hole-to-hole spacings composed of cylindrical and diffuser holes. For the first case, lateral and streamwise pitches are 7.5 times the diameter. For the second case, pitch-to-diameter ratio is 14 in lat
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Rhee, Dong Ho, Youn Seok Lee, and Hyung Hee Cho. "Film Cooling Effectiveness and Heat Transfer of Rectangular-Shaped Film Cooling Holes." In ASME Turbo Expo 2002: Power for Land, Sea, and Air. ASMEDC, 2002. http://dx.doi.org/10.1115/gt2002-30168.

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An experimental study has been conducted to measure the local film-cooling effectiveness and the heat transfer coefficient for a single row of rectangular-shaped holes. The holes have a 35° inclination angle with 3 hole diameter spacing of rectangular cross-sections. Four different cooling hole shapes such as a straight rectangular hole, a rectangular hole with laterally expanded exit, a circular hole and a two-dimensional slot are tested. The rectangular cross-section has the aspect ratio of 2 at the hole inlet with the hydraulic diameter of 10 mm. The area ratio of the exit to the hole inlet
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Kim, Sun-min, Ki-Don Lee, and Kwang-Yong Kim. "Numerical Study on Film-Cooling Effectiveness for Various Film-Cooling Hole Schemes." In ASME-JSME-KSME 2011 Joint Fluids Engineering Conference. ASMEDC, 2011. http://dx.doi.org/10.1115/ajk2011-22003.

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Film-cooling has been widely used as the important alternative to protect the turbine blade. Since the film-cooling hole geometry is one of the most influential parameters for film-cooling performance, various film-cooling hole schemes have been developed to increase cooling performance for the past few decades. In the present work, numerical analysis has been performed to investigate and to compare the film-cooling performance of various film-cooling hole schemes such as fan-shaped, crescent, louver, and dumbbell holes. For analyzes of the turbulent flow and film-cooling, three-dimensional Re
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Takeishi, Kenichiro, Yutaka Oda, Yuta Egawa, and Satoshi Hada. "Film Cooling With Swirling Coolant Flow Controlled by Impingement Cooling in a Closed Cavity." In ASME 2011 Power Conference collocated with JSME ICOPE 2011. ASMEDC, 2011. http://dx.doi.org/10.1115/power2011-55390.

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A new film cooling concept has been developed by managing the swirled film coolant induced inside a hexagonal plenum by two slant impingement jets, which are inclined at α degree toward the vertical direction and installed in a staggered position on the plenum chamber wall. Film cooling tests have been conducted by using a circular film cooling hole model mounted on a low speed wind tunnel. Heat transfer coefficient distributions of inclined jet impingements in a closed cavity was measured by naphthalene sublimation method and the film cooling effectiveness on the surface of the wind tunnel wa
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Holgate, Nicholas E., Peter T. Ireland, and Eduardo Romero. "The Effects of Combustor Cooling Features on Nozzle Guide Vane Film Cooling Experiments." In ASME Turbo Expo 2018: Turbomachinery Technical Conference and Exposition. American Society of Mechanical Engineers, 2018. http://dx.doi.org/10.1115/gt2018-75249.

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Recent advances in experimental methods have allowed researchers to study nozzle guide vane film cooling in the presence of combustor dilution ports and endwall films. The dilution injection creates nonuniformities in temperature, velocity, and turbulence, and an understanding of the vane film cooling performance is complicated by competing influences. In this study, dilution port temperature profiles have been measured in the absence of vane film cooling and compared to film effectiveness measurements in the presence of both films and dilution, illustrating the effects of the dilution port tu
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Reports on the topic "Film cooling"

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Wygnanski, Israel J., Alfonso Ortega, and Hermann Fasel. Film Cooling by a Pulsating Wall Jet. Defense Technical Information Center, 1997. http://dx.doi.org/10.21236/ada329651.

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Leylek, James H., D. K. Walters, William D. York, D. S. Holloway, and Jeffrey D. Ferguson. Computational Film Cooling Methods for Gas Turbine Airfoils. Defense Technical Information Center, 2002. http://dx.doi.org/10.21236/ada400186.

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Muss, Jeffrey. 5Klbf Unielement TCA for Film Cooling Model Validation. Defense Technical Information Center, 2003. http://dx.doi.org/10.21236/ada414443.

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Straub, Douglas, Andrew Tulgestke, Matthew Searle, and Edward Robey. Simple Heat Transfer Model for Film Cooling Applications. Office of Scientific and Technical Information (OSTI), 2025. https://doi.org/10.2172/2519681.

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Himansu, Ananda, Edward B. Coy, Venkateswaran Sankaran, and Steven A. Danczyk. Modeling of Fuel Film Cooling on Chamber Hot Wall. Defense Technical Information Center, 2014. http://dx.doi.org/10.21236/ada611830.

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Schauer, John J., and David J. Pestian. Film Cooling Heat Transfer with High Free Stream Turbulence. Defense Technical Information Center, 1995. http://dx.doi.org/10.21236/ada312458.

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Ramesh, Sridharan, and Douglas Straub. Film Cooling Performance Predictions For Air And Supercritical CO2. Office of Scientific and Technical Information (OSTI), 2021. http://dx.doi.org/10.2172/1827885.

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Coulthard, Sarah M. Effects of Pulsing on Film Cooling of Gas Turbine Airfoils. Defense Technical Information Center, 2005. http://dx.doi.org/10.21236/ada437128.

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9

Raben, Sam, Pavlos Vlachos, and Wing Ng. Effects of Leading Edge Film-Cooling and Surface Roughness on the Downstream Film-Cooling Along a Transonic Turbine Blade for Low and High Free-Stream Turbulence. Defense Technical Information Center, 2008. http://dx.doi.org/10.21236/ada479415.

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Bogard, David G., and Karen A. Thole. Improving Durability of Turbine Components Through Trenched Film Cooling and Contoured Endwalls. Office of Scientific and Technical Information (OSTI), 2014. http://dx.doi.org/10.2172/1224799.

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