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List of Tables 1.1 EU recommended relationships between annoyance and aircraft noise . . . . . 14 4.1 Main parameters of the CFD computation . . . . . . . . . . . . . . . . . . . . . . 68 5.1 Present operating regime (Mass flow ṁ in m 3 /h). . . . . . . . . . . . . . . . . . . 74 5.2 Main parameters of LES computation . . . . . . . . . . . . . . . . . . . . . . . . 76 5.3 The two computational grids under study . . . . . . . . . . . . . . . . . . . . . . 77 6.1 Wave coefficients definition . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 102 6.2 Mean flow inlet conditions and geometrical parameters . . . . . . . . . . . . . . 105 7.1 Eigen-Frequencies found by AVSP. Ardiden Combustor . . . . . . . . . . . . . . 125 10
Page 1: UNIVERSITE MONTPELLIER II SCIENCES
Page 5: An expert is a man who has made all
Page 8 and 9: Y gracias familia mía!!, que así
Page 11: Abstract Today, much of the current
Page 14 and 15: 4 CONTENTS 3.4.1 Preconditioning .
Page 16 and 17: List of Figures 1.1 Main sources of
Page 18 and 19: 8 LIST OF FIGURES 5.19 Acoustic ene
Page 23 and 24: 1 General Introduction Contents 1.1
Page 25 and 26: 1.1 Noise in a combustion chamber 1
Page 27 and 28: 1.2 Scope of the present work 17 fl
Page 29 and 30: 1.3 Organization of the manuscript
Page 31 and 32: 2.1 Introduction 21 In their experi
Page 33 and 34: 2.2 Direct Computation of noise thr
Page 35 and 36: 2.2 Direct Computation of noise thr
Page 37 and 38: 2.3 Hybrid computation of noise: Ac
Page 51 and 52: 3 Development of a numerical tool f
Page 53 and 54: 3.1 Discretizing the Phillips’ eq
Page 55 and 56: 3.1 Discretizing the Phillips’ eq
Page 57 and 58: 3.3 Solving the system Ax = b 47 [
Page 59 and 60: 3.3 Solving the system Ax = b 49 wh
Page 61 and 62: 3.3 Solving the system Ax = b 51 v
Page 63 and 64: 3.3 Solving the system Ax = b 53
Page 65 and 66: 3.4 GMRES 55 Stopping criteria of G
Page 67 and 68: 3.4 GMRES 57 FGMRES x 0 m =1 AẐm
Page 69 and 70: 4.1 Fundamental validation cases 59
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4.1 Fundamental validation cases 61
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4.1 Fundamental validation cases 63
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4.2 The 2D premixed laminar flame 6
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5.2 Experimental configuration 73 f
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5.3 Combustion noise Analysis 75 Mi
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5.3 Combustion noise Analysis 77
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5.3 Combustion noise Analysis 79 50
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5.3 Combustion noise Analysis 81 SP
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5.3 Combustion noise Analysis 83 Fi
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5.3 Combustion noise Analysis 85 Pr
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5.4 Filtering a LES pressure field
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5.4 Filtering a LES pressure field
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5.5 LES vs. Hybrid Results 91 400 H
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5.6 Conclusions 93 Ac. Energy (J)
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6 Boundary conditions for low Mach
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6.2 The quasi 1D Linearized Euler E
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6.3 The 1D linearized Euler equatio
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6.3 The 1D linearized Euler equatio
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6.4 Transmitted and reflected acous
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6.4 Transmitted and reflected acous
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6.5 When entropy does not remain co
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6.6 Transmitted and Reflected Waves
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7.2 Mean parameters of the Intake D
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7.3 Acoustic Evaluation 123 In the
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7.4 Helmholtz Solver Computation 12
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7.5 Conclusions 127 tion coefficien
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BIBLIOGRAPHY 129 [14] CHIU, H. H.,
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BIBLIOGRAPHY 131 [47] LEYKO, M., NI
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BIBLIOGRAPHY 133 [78] RAYLEIGH, L.
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A About the π c ′ = 0 assumption
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A.1 When is π T ′ equal to zero?
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B Publications In this appendix two
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141 Assessment of combustion noise
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143 d 2 π dt 2 − ∂ ( c 2 ∂π
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145 swirl motion in the D = 30 mm d
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147 wall. The ratio of the resolved
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149 50 x = 7 mm x = 17 mm 50 x = 27
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151 LES (AVBP) LES ASSUMPTION acous
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153 power is well captured by both
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155 [27] A. Lamraoui et al. “Acou
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157 required in addition to high-re
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159 flame/turbulence interactions a
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161 Observing with attention fig. ?
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163 SPL (dB) − micro 7 180 160 14
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