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Chapter 7: Computation of the Reflection Coefficient on the Inlet air circuit of an Helicopter combustor 124 chamber Module of R #'& # "'& " 0.948 ()*!+,-./01234-15)-61-7-.819*0::3*01;3
7.4 Helmholtz Solver Computation 125 INLET B.C Eigen-frequency Eigen-frequency IM (real part) (imaginary part) u ′ = 0 507.9 Hz -2.3 Hz Airline with total pressure jump 508.8 Hz -4.4Hz Airline without total pressure jump 508.5 Hz -4.6 Hz Table 7.1: Eigen-Frequencies found by AVSP. Ardi<strong>de</strong>n Combustor u ′ =0 Inlet u ′ =0 Inlet Outlet u ′ =0 Outlet u ′ =0 (a)| ˆp| (b) Arg( ˆp) Figure 7.6: Acoustic Mo<strong>de</strong> of the Aeroengine combustor. 507.9 Hz
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UNIVERSITE MONTPELLIER II SCIENCES
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An expert is a man who has made all
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Y gracias familia mía!!, que así
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Abstract Today, much of the current
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4 CONTENTS 3.4.1 Preconditioning .
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List of Figures 1.1 Main sources of
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8 LIST OF FIGURES 5.19 Acoustic ene
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List of Tables 1.1 EU recommended r
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14 Chapter 1: General Introduction
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2 Computation of noise generated by
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22 Chapter 2: Computation of noise
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42 Chapter 3: Development of a nume
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4 Validation of the acoustic code A
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60 Chapter 4: Validation of the aco
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5 Assessment of combustion noise in
Page 84 and 85: 74 Chapter 5: Assessment of combust
Page 106 and 107: 96 Chapter 6: Boundary conditions f
Page 108 and 109: 98 Chapter 6: Boundary conditions f
Page 110 and 111: 100 Chapter 6: Boundary conditions
Page 130 and 131: 7 Computation of the Reflection Coe
Page 132 and 133: Chapter 7: Computation of the Refle
Page 136 and 137: Chapter 7: Computation of the Refle
Page 138 and 139: Bibliography [1] AGARWAL, A., MORRI
Page 140 and 141: 130 BIBLIOGRAPHY [30] FRAYSSÉ, V.,
Page 142 and 143: 132 BIBLIOGRAPHY [62] NICOUD, F., B
Page 144 and 145: 134 BIBLIOGRAPHY [93] SENSIAU, C. S
Page 146 and 147: 136 Chapter A: About the π ′ c =
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Page 150 and 151: 140 Chapter B: Publications
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Page 156 and 157: 146 Chapter B: Publications Microph
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Page 166 and 167: 156 Chapter B: Publications Extract
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