Impact of fuel supply impedance and fuel staging on gas turbine ...

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Numerical simulation The length <strong>of</strong> the ducts are the distances from the upstream plane <strong>and</strong> from the downstream plane to the center <strong>and</strong> are equal to L u = 0.02 m <strong>and</strong> L d = 0.035 m, respectively. The resulting transfer matrix T f g center is represented in Fig. 6.28 <strong>and</strong> 6.29 138
7 Acoustic analysis Once the acoustic characteristics <strong>of</strong> the flame dynamics <strong>and</strong> the axial swirler are determined with the CFD/SI method, an acoustic network model <strong>of</strong> the combustion configuration can be set up. The setup <strong>of</strong> the model is part <strong>of</strong> the next section. With the network model the impact <strong>of</strong> the acoustic <strong>impedance</strong> on the thermo-acoustic stability is analyzed. Furthermore, it is shown how the location <strong>of</strong> the <strong>fuel</strong> injection nozzles influences the acoustics <strong>of</strong> the entire system, followed by the investigation <strong>of</strong> the impact <strong>of</strong> multiple <strong>fuel</strong> injection stages. From the results obtained, design guidelines are derived. 7.1 Setup <strong>of</strong> the acoustic network model The acoustic network model consists <strong>of</strong> the plenum, the mixing section, the <strong>fuel</strong> <strong>supply</strong>, the axial swirler <strong>and</strong> the combustion chamber. The acoustic characteristics <strong>of</strong> the combustor parts, like plenum or <strong>fuel</strong> <strong>supply</strong>, are represented by acoustic elements, e.g. acoustic boundary conditions, simple ducts, area changes <strong>and</strong> ”T-junctions”. The analytic relations <strong>of</strong> the acoustic elements were derived in chapter 3.3. The flame dynamics obtained by CFD/SI is implemented using the practical premixed flame element (chapter 3.3). The acoustic characteristics <strong>of</strong> the axial swirler are represented by a transfer matrix, which was also determined by CFD/SI as shown in chapter 6.4. As in the numerical analysis, two basic configurations are considered with two <strong>and</strong> three <strong>fuel</strong> injection stages, respectively. They are denoted again as case A <strong>and</strong> B. The structure <strong>of</strong> the acoustic network model <strong>of</strong> the combustion test rig with two <strong>fuel</strong> injection stages is presented in Fig. 7.1. Here, the names, e.g. ”Plenum”, ”AC I”, ”Mixing section I” are the names <strong>of</strong> the individual elements <strong>of</strong> the combustor network model, whereas their colors (see legend in Fig. 7.1) define the types <strong>of</strong> the acoustic elements, e.g. simple duct, area change,etc. The network 139
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Technische Universität München In
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und ihre Geduld besonders für die
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Contents 1 Introduction 1 1.1 Techn
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CONTENTS 7.2.2 Impact</stro
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Nomenclature G stretch factor [-] h
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Nomenclature λ air-fuel</s
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1 Introduction 1.1 Technology backg
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1.2 Thermo-acoustic instabilities 1
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1.2 Thermo-acoustic instabilities d
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1.3 Control of the
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1.3 Control of the
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1.4 Intention and
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1.5 Terminology and</strong
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1.5 Terminology and</strong
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2 Numerical analysis of</st
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2.1 Overview of me
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2.1 Overview of me
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2.1 Overview of me
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2.2 Flame dynamics of</stro
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2.3 Identification of</stro
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3 Acoustics Before analyzing the ac
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3.1 Basic acoustic equations as a f
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3.2 Linear acoustic equations Here,
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3.2 Linear acoustic equations p ′
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3.3 Acoustic network model p ′ (x
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3.3 Acoustic network model matrix e
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3.3 Acoustic network model The <str
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3.3 Acoustic network model where A
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3.3 Acoustic network model coming c
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3.3 Acoustic network model Z i Air
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3.3 Acoustic network model pressure
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3.3 Acoustic network model The eige
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3.3 Acoustic network model tine. To
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4 Modeling of turb
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4.1 Theory and num
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4.1 Theory and num
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4.2 Theoretical and</strong
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5 System Identification Flame trans
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5.1 Model structures and</s
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5.2 System Identification 5.2 Syste
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Page 107 and 108: 5.5 Proof
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Page 121 and 122: 6.1 Practical premixed combustor co
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Page 133 and 134: 6.3 Identifiction of</stron
Page 149 and 150: 6.4 Identification of</stro
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Page 157 and 158: 7.2 Acoustic network model results
Page 181 and 182: 8 Summary and Conc
Page 183 and 184: The flame element of</stron
Page 185 and 186: Bibliography [1] Verband</s
Page 187 and 188: BIBLIOGRAPHY [18] L. Crocco. Theore
Page 189 and 190: BIBLIOGRAPHY [36] A. Giauque, L. Se
Page 191 and 192: BIBLIOGRAPHY [54] J.J. Keller, W. E
Page 193 and 194: BIBLIOGRAPHY [72] T. Lieuwen <stron
Page 195 and 196: BIBLIOGRAPHY Number 98-GT-269 in In
Page 197 and 198: BIBLIOGRAPHY [112] T. Sattelmayer.
Page 199 and 200: BIBLIOGRAPHY [130] A. Widenhorn. pr
Page 201 and 202: A.2 Estimation of
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A.3 Main flow parameters an
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Impact of fuel supply impedance and fuel staging on gas turbine ...

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