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BIBLIOGRAPHIE ERIKSEN, V. L. & GOLDSTEIN, R. J. 1974a Heat transfer and film cooling following injection through inclined circular tubes. J. Heat Transf. 96, 239–245. ERIKSEN, V. L. & GOLDSTEIN, R. J. 1974b Heat transfer and film cooling following normal injection through a round hole. J. Eng. for Power pp. 1–6. ERRERA, M. P. & CHEMIN, S. 2004 A fluid-solid thermal coupling applied to an effusion cooling system. In 34th Fluid Dynamics Conference and Exhibit. Portland, Oregon. FERZIGER, J.H. & PERIĆ, M. 1997 Computational Methods for Fluid Dynamics. Berlin, Heidelberg, New York : Springer Verlag. FOULON, C. 1999 Étude numérique et expérimentale du comportement thermique d’une paroi multiperforée mince. Application au refroidissement pariétal des chambres de combustion des moteurs aéronautiques. Thèse d’Université, Université de Poitiers. FREITAG, M. & JANICKA, J. 2007 Investigation of a strongly swirled premixed flame using les. Proc. Combust. Inst. 31, 1477–1485. FRIC, T.F. & ROSHKO, A. 1994 Vortical structure in the wake of a transverse jet. J. Fluid Mech. 279, 1–47. GERMANO, M., PIOMELLI, U., MOIN, P. & CABOT, W. 1991 A dynamic subgrid-scale eddy viscosity model. Phys. Fluids 3 (7), 1760–1765. GLEZER, A. & AMITAY, M. 2002 Synthetic jets. Annu. Rev. Fluid Mech. 34, 503–529. GOLDSTEIN, R. J. 1971 Advances in Heat Transfer. Academic Press, New-York and London. GOLDSTEIN, R. J., ECKERT, E. R. G., ERIKSEN, V. L. & RAMSEY, J. W. 1969 Film cooling following injection through inclined circular tubes. NASA CR-72612 . GOLDSTEIN, R. J., ECKERT, E. R. G. & RAMSEY, J. W. 1968 Film cooling with injection through holes : adiabatic wall temperatures downstream of a circular hole. J. Eng. for Power 90, 383–395. GOURDAIN, N. 2005 Simulation numérique des phénomènes de décollement tournant dans les compresseurs axiaux. Thèse d’Université, Ecole Centrale Lyon. GRITSCH, M., SCHULTZ, A. & WITTIG, S. 2001 Effect of crossflows on the discharge coefficient of film cooling holes with varying angles of inclination and orientation. ASME J. Turbomach. 123, 781– 787. GUSTAFSSON, K. M. B. 2001 Experimental studies of effusion cooling. Thèse d’Université, Chalmers University of Technology. Göteborg. HAH, C., BERGNER, J. & SCHIFFER, H.-P. 2006 Short length-scale rotating stall inception in a transonic axial compressor – Criteria and mechanisms. In Proceedings of GT2006 ASME Turbo Expo 2006 : Power for Land, Sea and Air May 8-11, 2006, Barcelona, Spain. 184
BIBLIOGRAPHIE HALE, C. A., PLESNIAK, M. W. & RAMADHYANI, S. 2000a Film cooling effectiveness for short film cooling holes fed by a narrow plenum. ASME J. Turbomach. 122, 553–557. HALE, C. A., PLESNIAK, M. W. & RAMADHYANI, S. 2000b Structural features and surface heat transfer associated with a row of short-hole jets in crossflow. Int. J. Heat Fluid Flow 21, 542–553. HAM, F., APTE, S. V., IACCARINO, G., WU, X., HERRMANN, M., CONSTANTINESCU, G., MA- HESH, K. & MOIN, P. 2003 Unstructured LES of reacting multiphase flows in realistic gas turbine combustors. In Center for Turbulence Research, Annual Research Briefs. HAM, F. & IACCARINO, G. 2004 Energy conservation in collocated discretization schemes on unstructured meshes. In Center for Turbulence Research, Annual Research Briefs, pp. 3–14. HAM, F., MATSSON, K. & IACCARINO, G. 2006 Accurate and stable finite volume operators for unstructured flow solvers. In Center for Turbulence Research, Annual Research Briefs, pp. 243–261. HARRINGTON, M. K, MCWATERS, M. A., BOGARD, D. G., A., LEMMON C. & THOLE, K. A. 2001 Full-coverage film cooling with short normal injection holes. ASME TURBOEXPO 2001. 2001-GT- 0130 . HAY, N. & LAMPARD, D. 1998 Discharge coefficient of turbines cooling holes. ASME J. Turbomach. 120, 314–319. HIRSCH, C. 1988 Numerical Computation of internal and external flows. New York : John Wiley. HUANG, Y., S., WANG & YANG, V. 2006 Systematic analysis of lean-premixed swirl-stabilized combustion. AIAA J. 44 (724-740). HYAMS, D. G. & LEYLEK, J.H. 2000 A detailed analysis of film-cooling physics : Part 3- streamwise injection with shaped holes. ASME J. Turbomach. 122, 122–132. IOUROKINA, I. V. & LELE, S. K. 2006 Large eddy simulation of film-cooling above the flat surface with a large plenum and short exit holes. In 44th Aerospace Sciences Meeting and Exhibit. JAMESON, A., SCHMIDT, W. & TURKEL, E. 1981 Numerical solution of the Euler equations by finite volume methods using Runge-Kutta time stepping schemes. In 14th Fluid and Plasma Dynamic Conference (ed. AIAA paper 81-1259). Palo Alto. JANUS, B., DREIZLER, A. & JANICKA, J. 2007 Experiments on swirl stabilized non premixed natural gas flame in a model gas turbine combustor. Proc. Combust. Inst. 31 (3091-3098). JIMÉNEZ, J. & MOIN, P. 1991 The minimal flow unit in near-wall turbulence. J. Fluid Mech. 225, 213–240. JOVANOVIC, M. B., DE LANGE, H. C. & VAN STEENHOVEN, A. A. 2006 Influence of hole imperfection on jet cross flow interaction. Int. J. Heat Fluid Flow . KADOTAMI, K. & GOLDSTEIN, R. J. 1979 On the nature of jets entering a turbulent flow. Part b - film cooling performance. J. Heat Transf. 101, 355–362. 185
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UNIVERSITE MONTPELLIER II SCIENCES
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Table des matières Remerciements 7
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Remerciements Cette thèse a été
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Liste des symboles Lettres romaines
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Introduction générale La volonté
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Chapitre 1 Contexte industriel et s
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1.1 Les turbines à gaz pour les tu
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1.1 Les turbines à gaz a) b) GAZ C
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1.2 La simulation numérique des é
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1.3 Objectifs et plan de la thèse
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Chapitre 2 L’écoulement autour d
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2.1 Présentation de la configurati
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2.2 Perte de charge au passage d’
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2.3 La multi-perforation : aspects
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2.4 Caractérisation aérodynamique
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2.5 Modélisation de la multi-perfo
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Chapitre 3 Simulations des grandes
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3.2 Simulations des Grandes Echelle
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3.3 Le code de calcul AVBP 3.3.1 As
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3.3 Le code de calcul AVBP dans le
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3.3 Le code de calcul AVBP de sa st
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Chapitre 4 Simulations numériques
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4.1 Quelles simulations pour la mod
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4.2 Choix de la méthode de simulat
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4.2 Choix de la méthode de simulat
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4.3 Sensibilité des simulations au
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Chapitre 5 Simulations numériques
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2 S. Mendez and F. Nicoud COMBUSTIO
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4 S. Mendez and F. Nicoud (c) The i
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6 S. Mendez and F. Nicoud CALCULATI
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8 S. Mendez and F. Nicoud Name Numb
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10 S. Mendez and F. Nicoud x/d z/d
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12 S. Mendez and F. Nicoud main, it
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14 S. Mendez and F. Nicoud 1.0 a 1.
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16 S. Mendez and F. Nicoud ROWS 1 3
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18 S. Mendez and F. Nicoud Figure 1
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20 S. Mendez and F. Nicoud 30 ◦ 3
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22 S. Mendez and F. Nicoud & Mahesh
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28 S. Mendez and F. Nicoud film, th
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30 S. Mendez and F. Nicoud Region t
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32 S. Mendez and F. Nicoud Expressi
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34 S. Mendez and F. Nicoud geometri
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Page 137 and 138: Chapitre 6 Un modèle adiabatique p
Page 139 and 140: ρ Mass density, kg/m 3 P T V i τ
Page 141 and 142: cence of the jets. This is particul
Page 143 and 144: Simulations. The small-scale LES re
Page 145 and 146: chosen to compare with numerical re
Page 147 and 148: pressure drop of 41 Pa is effective
Page 149 and 150: Region total plate hole solid wall
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Page 153 and 154: V U σ V inj jet cotan(α′ ) V U
Page 155 and 156: PERIODIC Z INFLOW 1 WALL 24 OUTFLOW
Page 157 and 158: part of the plate. Downstream of th
Page 159 and 160: streamwise momentum flux. As a cons
Page 161 and 162: 8 Fric, T. and Roshko, A., “Vorti
Page 163 and 164: Discussion sur la modélisation de
Page 165 and 166: 20 15 10 y/d 5 0 -5 -10 0.0 0.2 0.4
Page 167 and 168: Chapitre 7 Simulations numériques
Page 169 and 170: Primary flow (burnt gases) Secondar
Page 171 and 172: Figure 7: Nusselt number over the s
Page 173 and 174: the perforated plate. A Large-Eddy
Page 175 and 176: Les tableaux de flux permettent de
Page 177 and 178: Conclusion générale Dans cette é
Page 179 and 180: Conclusion générale En ce qui con
Page 181 and 182: Bibliographie AKSELVOLL, K. & MOIN,
Page 183: BIBLIOGRAPHIE CORON, X. 2001 Étude
Page 187 and 188: BIBLIOGRAPHIE LIEUWEN, T. & YANG, V
Page 189 and 190: BIBLIOGRAPHIE MOST, A. & BRUEL, P.
Page 191 and 192: BIBLIOGRAPHIE SCHILDKNECHT, M., MIL
Page 193: Annexes
Page 196 and 197: ARTIFICIAL VISCOSITY MODELS A.2.1 T
Page 198 and 199: ARTIFICIAL VISCOSITY MODELS - 4 th
Page 200 and 201: ARTIFICIAL VISCOSITY MODELS As a co
Page 202: ARTIFICIAL VISCOSITY MODELS 202
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