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Format: 1 Online-Ressource (IX, 419 Seiten)

Edition: 1st ed. 2021

ISBN: 9783030538477

Series Statement: Notes on Numerical Fluid Mechanics and Multidisciplinary Design 146

Additional Edition: Erscheint auch als Druck-Ausgabe ISBN 978-3-030-53846-0

Additional Edition: Erscheint auch als Druck-Ausgabe ISBN 978-3-030-53848-4

Additional Edition: Erscheint auch als Druck-Ausgabe ISBN 978-3-030-53849-1

Language: English

DOI: 10.1007/978-3-030-53847-7

URL: Volltext  (kostenfrei)

URL: Volltext  (kostenfrei)

UID:

Format: 1 online resource (ix, 419 pages 273) : , illustrations in color

Edition: 1st edition.

ISBN: 978-3-030-53847-7 , 3-030-53847-8

Series Statement: Notes on Numerical Fluid Mechanics and Multidisciplinary Design, 146

Content: This open access book presents the findings of Collaborative Research Center Transregio 40 (TRR40), initiated in July 2008 and funded by the German Research Foundation (DFG). Gathering innovative design concepts for thrust chambers and nozzles, as well as cutting-edge methods of aft-body flow control and propulsion-component cooling, it brings together fundamental research undertaken at universities, testing carried out at the German Aerospace Center (DLR) and industrial developments from the ArianeGroup. With a particular focus on heat transfer analyses and novel cooling concepts for thermally highly loaded structures, the book highlights the aft-body flow of the space transportation system and its interaction with the nozzle flow, which are especially critical during the early phase of atmospheric ascent. Moreover, it describes virtual demonstrators for combustion chambers and nozzles, and discusses their industrial applicability. As such, it is a timely resource for researchers, graduate students and practitioners. .

Note: Collaborative Research for Future Space Transportation Systems -- Innovative Cooling for Rocket Combustion Chambers -- Film Cooling in Rocket Nozzle -- Heat Transfer in Pulsating Flow and its Impact on Temperature Distribution and Damping Performance of Acoustic Resonators -- Effects of a Launcher’s External Fow on a Dual-Bell Nozzle Flow -- Interaction of Wake and Propulsive Jet Flow of a Generic Space Launcher -- Numerical Analysis of the Turbulent Wake for a Generic Space Launcher with a Dual-Bell Nozzle.

Additional Edition: ISBN 3-030-53846-X

Language: English

Keywords: Electronic books.

DOI: 10.1007/978-3-030-53847-7

URL: Click here to view book

URL: lizenzpflichtig

UID:

Format: 1 Online-Ressource (419 p.)

ISBN: 9783030538477

Series Statement: Notes on Numerical Fluid Mechanics and Multidisciplinary Design

Content: This open access book presents the findings of Collaborative Research Center Transregio 40 (TRR40), initiated in July 2008 and funded by the German Research Foundation (DFG). Gathering innovative design concepts for thrust chambers and nozzles, as well as cutting-edge methods of aft-body flow control and propulsion-component cooling, it brings together fundamental research undertaken at universities, testing carried out at the German Aerospace Center (DLR) and industrial developments from the ArianeGroup. With a particular focus on heat transfer analyses and novel cooling concepts for thermally highly loaded structures, the book highlights the aft-body flow of the space transportation system and its interaction with the nozzle flow, which are especially critical during the early phase of atmospheric ascent. Moreover, it describes virtual demonstrators for combustion chambers and nozzles, and discusses their industrial applicability. As such, it is a timely resource for researchers, graduate students and practitioners

Note: English

Language: English

URL: kostenfrei

UID:

Format: 164 S. : Ill., graph. Darst.

Note: Karlsruhe, Univ., Diss.

Language: German

Keywords: Flüssigkeit ; Zerstäubung ; Flüssigkeit ; Zerstäubung ; Hochschulschrift ; Luft-Flüssigkeitsfilm-Störung ; Filmzerfall

UID:

Format: 164 S. , Ill., graph. Darst.

Note: Karlsruhe, Univ., Diss.

Language: German

Keywords: Flüssigkeit ; Zerstäubung ; Flüssigkeit ; Zerstäubung ; Luft-Flüssigkeitsfilm-Störung ; Filmzerfall ; Hochschulschrift ; Filmzerfall ; Luft-Flüssigkeitsfilm-Störung

UID:

Format: IX, 419 p. 273 illus., 213 illus. in color. , online resource.

Edition: 1st ed. 2021.

ISBN: 9783030538477

Series Statement: Notes on Numerical Fluid Mechanics and Multidisciplinary Design, 146

Content: This open access book presents the findings of Collaborative Research Center Transregio 40 (TRR40), initiated in July 2008 and funded by the German Research Foundation (DFG). Gathering innovative design concepts for thrust chambers and nozzles, as well as cutting-edge methods of aft-body flow control and propulsion-component cooling, it brings together fundamental research undertaken at universities, testing carried out at the German Aerospace Center (DLR) and industrial developments from the ArianeGroup. With a particular focus on heat transfer analyses and novel cooling concepts for thermally highly loaded structures, the book highlights the aft-body flow of the space transportation system and its interaction with the nozzle flow, which are especially critical during the early phase of atmospheric ascent. Moreover, it describes virtual demonstrators for combustion chambers and nozzles, and discusses their industrial applicability. As such, it is a timely resource for researchers, graduate students and practitioners. .

Note: Collaborative Research for Future Space Transportation Systems -- Innovative Cooling for Rocket Combustion Chambers -- Film Cooling in Rocket Nozzle -- Heat Transfer in Pulsating Flow and its Impact on Temperature Distribution and Damping Performance of Acoustic Resonators -- Effects of a Launcher's External Fow on a Dual-Bell Nozzle Flow -- Interaction of Wake and Propulsive Jet Flow of a Generic Space Launcher -- Numerical Analysis of the Turbulent Wake for a Generic Space Launcher with a Dual-Bell Nozzle.

In: Springer Nature eBook

Additional Edition: Printed edition: ISBN 9783030538460

Additional Edition: Printed edition: ISBN 9783030538484

Additional Edition: Printed edition: ISBN 9783030538491

Language: English

DOI: 10.1007/978-3-030-53847-7

URL: https://doi.org/10.1007/978-3-030-53847-7

UID:

Format: 1 online resource (409 pages)

ISBN: 9783030538477

Series Statement: Notes on Numerical Fluid Mechanics and Multidisciplinary Design Ser. ; v.146

Note: Intro -- Preface -- Contents -- Collaborative Research for Future Space Transportation Systems -- 1 Introduction -- 2 Research Area A: Structural Cooling -- 2.1 Transpiration Cooled Ceramic Structures -- 2.2 Supersonic Film Cooling -- 2.3 Damping Performance of Resonators -- 3 Research Area B: Aft-Body Flows -- 3.1 Nozzle Flow Separation Studies -- 3.2 Interaction of Rocket Plume and External Flow -- 3.3 Modeling of Buffeting -- 4 Research Area C: Combustion Chamber -- 4.1 Dynamic Processes in Trans-Critical Jets -- 4.2 Injection, Mixing and Combustion Under Real-Gas Conditions -- 4.3 Boundary Layer Heat Transfer Modelling -- 4.4 Combustion Stability of Rocket Engines -- 5 Research Area D: Thrust Nozzle -- 5.1 Thermal Barrier Coatings and Component Life Prediction -- 5.2 Cooling Channel Flows -- 5.3 Fluid Structure Interaction -- 6 Research Area K: Thrust-Chamber Assembly -- 6.1 Combustion and Heat Transfer -- 6.2 Dual Bell Nozzle -- 6.3 Thrust-Chamber Demonstrators -- 7 Central Research and Education Support -- References -- Structural Cooling -- A Coupled Two-Domain Approach for Transpiration Cooling -- 1 Motivation -- 2 Mathematical Modeling -- 2.1 Hot Gas Domain -- 2.2 Porous Medium Domain -- 2.3 Coupling Conditions -- 3 Numerical Methods -- 4 Numerical Results -- 4.1 Non-uniform Injection into a Subsonic Hot Gas Channel Flow -- 4.2 Uniform Injection into a Supersonic Nozzle Flow -- 5 Conclusion -- References -- Innovative Cooling for Rocket Combustion Chambers -- 1 Introduction -- 2 Experimental Setup -- 2.1 Stacked Transpiration Cooling Specimen -- 2.2 Hot Gas Channel and Measurement Setup -- 3 Numerical Setup -- 4 Results and Interpretation of the Serial Transpiration Cooling Experiment -- 5 Summary and Outlook -- References -- Film Cooling in Rocket Nozzles -- 1 Motivation -- 2 Film Cooling Theory -- 2.1 Film Cooling Efficiency. , 2.2 Film Cooling Model -- 3 Experimental Setup -- 3.1 Test Facility -- 4 Results Conical Nozzle -- 4.1 Reference Flow -- 4.2 Parametric Study -- 4.3 Correlation -- 5 Results Dual-Bell Nozzle -- 5.1 Experiments Without Film Cooling -- 5.2 Experiments with Film Cooling -- 6 Conclusion -- References -- Numerical Simulation of Film Cooling in Supersonic Flow -- 1 Introduction -- 2 Flow Configuration -- 2.1 Film Cooling -- 3 Numerical Method -- 4 Results -- 4.1 Influence of Coolant Mass Flow Rate -- 4.2 Influence of Coolant Mach Number -- 4.3 Influence of the Upstream Wall Temperature -- 4.4 Lip-Thickness Influence -- 4.5 Influence of the Coolant Velocity Profile -- 4.6 Correlation of Data -- 5 Conclusions and Outlook -- References -- Heat Transfer in Pulsating Flow and Its Impact on Temperature Distribution and Damping Performance of Acoustic Resonators -- 1 Introduction and Placement in SFB -- 2 Impact of Temperature Inhomogeneities on Damping Performance -- 3 Impact of Acoustic Oscillations on Heat Transfer -- 3.1 Wall Normal Heat Transfer -- 3.2 Longitudinal Heat Transfer -- 4 Summary and Conclusions -- References -- Aft-Body Flows -- Effects of a Launcher's External Flow on a Dual-Bell Nozzle Flow -- 1 Introduction -- 2 Experimental Setup -- 2.1 BFS Model -- 2.2 Measurement Techniques -- 3 Results -- 3.1 Steady-State Sea Level Mode -- 3.2 Steady-State Altitude Mode -- 3.3 Transition -- 4 Summary and Conclusions -- References -- Interaction of Wake and Propulsive Jet Flow of a Generic Space Launcher -- 1 Introduction -- 2 Experimental and Numerical Setup -- 2.1 Geometry and Test Cases -- 2.2 Experimental Setup -- 2.3 Numerical Setup -- 3 Results -- 3.1 Passive Flow Control on TIC Configuration -- 3.2 Analysis of Dual-Bell Transition-Effect of Reynolds Number -- 3.3 Analysis of Dual-Bell Transition-Influence of Afterbody Geometry -- 4 Summary. , References -- Rocket Wake Flow Interaction Testing in the Hot Plume Testing Facility (HPTF) Cologne -- 1 Introduction -- 2 The Hot Plume Testing Facility (HPTF) -- 2.1 Vertical Wind Tunnel Cologne (VMK) -- 2.2 GH2/GO2 Supply Facility -- 3 Characterization of HPTF for Wind Tunnel Testing -- 3.1 HPTF Characterization Test Setup -- 3.2 HPTF Characterization Test Results -- 4 Cold and Hot Plume Interaction Testing -- 4.1 GH2/GO2 Wind Tunnel Model -- 4.2 Test Program and Test Conditions -- 4.3 Wind Tunnel Test Results -- 5 Conclusions -- References -- Numerical Analysis of the Turbulent Wake for a Generic Space Launcher with a Dual-Bell Nozzle -- 1 Introduction -- 2 Computational Approach -- 2.1 Geometry and Flow Conditions -- 2.2 Zonal RANS/LES Flow Solver -- 2.3 Computational Mesh -- 3 Results -- 3.1 Supersonic Configuration -- 3.2 Transonic Configuration -- 4 Conclusions -- References -- Numerical Investigation of Space Launch Vehicle Base Flows with Hot Plumes -- 1 Introduction -- 2 Numerical Method and Setup -- 3 Results of Thermal Flow Structure Coupling -- 4 Investigation of Aft-Body Flow Fields -- 5 Conclusions and Outlook -- References -- Combustion Chamber -- On the Consideration of Diffusive Fluxes Within High-Pressure Injections -- 1 Introduction -- 2 Phenomenological Considerations on Mixing Jets -- 3 Numerical Consideration and Thermodynamic Modeling -- 3.1 Thermodynamic Modeling -- 4 Numerical Results: LES of N-Hexane/Nitrogen Jet -- 5 Conclusions -- References -- Numerical Investigation of Injection, Mixing and Combustion in Rocket Engines Under High-Pressure Conditions -- 1 Introduction -- 2 Physical and Mathematical Modeling -- 2.1 Governing Equations -- 2.2 Numerical Flow Solver -- 2.3 Thermodynamic Modeling -- 2.4 Combustion Modeling -- 3 Results and Discussion -- 3.1 Thermodynamics -- 3.2 Combustion -- 4 Conclusion -- References. , Large-Eddy Simulations for the Wall Heat Flux Prediction of a Film-Cooled Single-Element Combustion Chamber -- 1 Introduction -- 2 Governing Equations and Numerical Procedure -- 3 Test Case -- 3.1 Combustion Chamber Test Cases -- 3.2 Roughness Test Cases -- 4 Results -- 4.1 Combustion Chamber Results -- 4.2 Roughness Results -- 5 Conclusions -- References -- Calculation of the Thermoacoustic Stability of a Main Stage Thrust Chamber Demonstrator -- 1 Introduction -- 2 Test Case -- 3 Stability Assessment Procedure -- 3.1 Perturbation Analysis -- 3.2 Mean Flow -- 3.3 Flame Response -- 3.4 External Components and Design Adaption -- 4 Numerical Setup -- 4.1 Eigensolution Study -- 4.2 Single Flame -- 5 Results -- 5.1 Dome Acoustics -- 5.2 Coupled Acoustics -- 5.3 Stability Behavior -- 6 Conclusions -- References -- Experimental Investigation of Injection-Coupled High-Frequency Combustion Instabilities -- 1 Introduction -- 1.1 Summary of Previous Investigations -- 2 Experimental Technique -- 2.1 Experimental Setup -- 2.2 Methodology -- 3 Results and Discussion -- 3.1 Mean Flame Images -- 3.2 Dynamic Characteristics -- 3.3 LOX Core Dynamic Response to Excited Injector Eigenmodes -- 3.4 Damping Device to Reduce Risk of Injection-Coupled Instabilities -- 4 Summary and Conclusions -- References -- Thrust Nozzle -- Pseudo-transient 3D Conjugate Heat Transfer Simulation and Lifetime Prediction of a Rocket Combustion Chamber -- 1 Introduction -- 2 Conjugate Heat Transfer Simulation -- 2.1 Computational Model -- 2.2 Results and Validation -- 3 Lifetime Prediction -- 3.1 Transient Thermal Analysis -- 3.2 Quasi-static Mechanical Analysis -- 4 Conclusion -- References -- Lifetime Experiments of Regeneratively Cooled Rocket Combustion Chambers and PIV Measurements in a High Aspect Ratio Cooling Duct -- 1 Introduction -- 2 Fatigue Experiment -- 2.1 Experimental Set-Up. , 2.2 Load Conditions -- 2.3 Load Phases -- 2.4 Deformations and Lifetime -- 3 Cooling Channel Measurements -- 3.1 Test Setup -- 3.2 Light Sheet Alignment -- 3.3 Window Size Analysis -- 3.4 Particle Shift -- 4 Conclusions -- References -- Mechanical Integrity of Thermal Barrier Coatings: Coating Development and Micromechanics -- 1 Introduction -- 2 Methods -- 2.1 Coating Process -- 2.2 Arc Heated Hypersonic Wind Tunnel -- 2.3 Subscale Combustion Chamber -- 3 Coating Design for a Large Scale Combustion Chamber -- 3.1 Mechanical Loads -- 3.2 Crack Propagation -- 4 Validation Tests -- 4.1 Arc Heated Hypersonic Wind Tunnel -- 4.2 Subscale Combustion Chamber -- 5 Conclusions -- References -- Assessment of RANS Turbulence Models for Straight Cooling Ducts: Secondary Flow and Strong Property Variation Effects -- 1 Introduction -- 2 High Aspect Ratio Cooling Duct -- 2.1 Equation System and Numerical Model -- 2.2 Simulation Setup -- 2.3 Flow and Temperature Field -- 3 Channel Flow with Strong Property Variations -- 3.1 Equation System and Numerical Model -- 3.2 Simulation Setup -- 3.3 Flow and Temperature Field -- 4 Summary and Conclusion -- References -- Experiments on Aerothermal Supersonic Fluid-Structure Interaction -- 1 Introduction -- 1.1 FSI and SWBLI -- 1.2 High Temperature FSI -- 2 Experiments on Aerothermoelastic FSI with SWBLI -- 2.1 Wind Tunnel H2K -- 2.2 Wind Tunnel Model and Instrumentation -- 2.3 Properties of the Elastic Panel -- 2.4 Experimental Results -- 3 Experiments on High Temperature FSI with Plastic Deformation -- 3.1 Arc-Heated Wind Tunnel L3K -- 3.2 Wind Tunnel Model and Instrumentation -- 3.3 Experimental Results -- 4 Conclusion -- References -- Numerical Modelling of Fluid-Structure Interaction for Thermal Buckling in Hypersonic Flow -- 1 Introduction -- 2 Fluid-Structure Interaction -- 3 Structural Model -- 3.1 Thermal Analysis. , 3.2 Structural Analysis.

Additional Edition: Print version: Adams, Nikolaus A. Future Space-Transport-System Components under High Thermal and Mechanical Loads Cham : Springer International Publishing AG,c2020 ISBN 9783030538460

Language: English

Keywords: Electronic books.

URL: Click to View

UID:

Format: 1 online resource (ix, 419 pages 273) : , illustrations in color

Edition: 1st edition.

ISBN: 978-3-030-53847-7 , 3-030-53847-8

Series Statement: Notes on Numerical Fluid Mechanics and Multidisciplinary Design, 146

Content: This open access book presents the findings of Collaborative Research Center Transregio 40 (TRR40), initiated in July 2008 and funded by the German Research Foundation (DFG). Gathering innovative design concepts for thrust chambers and nozzles, as well as cutting-edge methods of aft-body flow control and propulsion-component cooling, it brings together fundamental research undertaken at universities, testing carried out at the German Aerospace Center (DLR) and industrial developments from the ArianeGroup. With a particular focus on heat transfer analyses and novel cooling concepts for thermally highly loaded structures, the book highlights the aft-body flow of the space transportation system and its interaction with the nozzle flow, which are especially critical during the early phase of atmospheric ascent. Moreover, it describes virtual demonstrators for combustion chambers and nozzles, and discusses their industrial applicability. As such, it is a timely resource for researchers, graduate students and practitioners. .

Note: Collaborative Research for Future Space Transportation Systems -- Innovative Cooling for Rocket Combustion Chambers -- Film Cooling in Rocket Nozzle -- Heat Transfer in Pulsating Flow and its Impact on Temperature Distribution and Damping Performance of Acoustic Resonators -- Effects of a Launcher’s External Fow on a Dual-Bell Nozzle Flow -- Interaction of Wake and Propulsive Jet Flow of a Generic Space Launcher -- Numerical Analysis of the Turbulent Wake for a Generic Space Launcher with a Dual-Bell Nozzle.

Additional Edition: ISBN 3-030-53846-X

Language: English

DOI: 10.1007/978-3-030-53847-7

UID:

Format: 1 online resource (ix, 419 pages 273) : , illustrations in color

Edition: 1st edition.

ISBN: 978-3-030-53847-7 , 3-030-53847-8

Series Statement: Notes on Numerical Fluid Mechanics and Multidisciplinary Design, 146

Content: This open access book presents the findings of Collaborative Research Center Transregio 40 (TRR40), initiated in July 2008 and funded by the German Research Foundation (DFG). Gathering innovative design concepts for thrust chambers and nozzles, as well as cutting-edge methods of aft-body flow control and propulsion-component cooling, it brings together fundamental research undertaken at universities, testing carried out at the German Aerospace Center (DLR) and industrial developments from the ArianeGroup. With a particular focus on heat transfer analyses and novel cooling concepts for thermally highly loaded structures, the book highlights the aft-body flow of the space transportation system and its interaction with the nozzle flow, which are especially critical during the early phase of atmospheric ascent. Moreover, it describes virtual demonstrators for combustion chambers and nozzles, and discusses their industrial applicability. As such, it is a timely resource for researchers, graduate students and practitioners. .

Note: Collaborative Research for Future Space Transportation Systems -- Innovative Cooling for Rocket Combustion Chambers -- Film Cooling in Rocket Nozzle -- Heat Transfer in Pulsating Flow and its Impact on Temperature Distribution and Damping Performance of Acoustic Resonators -- Effects of a Launcher’s External Fow on a Dual-Bell Nozzle Flow -- Interaction of Wake and Propulsive Jet Flow of a Generic Space Launcher -- Numerical Analysis of the Turbulent Wake for a Generic Space Launcher with a Dual-Bell Nozzle.

Additional Edition: ISBN 3-030-53846-X

Language: English

DOI: 10.1007/978-3-030-53847-7

UID:

Format: 1 online resource (409 pages)

ISBN: 9783030538477

Series Statement: Notes on Numerical Fluid Mechanics and Multidisciplinary Design Ser. v.146

Note: Intro -- Preface -- Contents -- Collaborative Research for Future Space Transportation Systems -- 1 Introduction -- 2 Research Area A: Structural Cooling -- 2.1 Transpiration Cooled Ceramic Structures -- 2.2 Supersonic Film Cooling -- 2.3 Damping Performance of Resonators -- 3 Research Area B: Aft-Body Flows -- 3.1 Nozzle Flow Separation Studies -- 3.2 Interaction of Rocket Plume and External Flow -- 3.3 Modeling of Buffeting -- 4 Research Area C: Combustion Chamber -- 4.1 Dynamic Processes in Trans-Critical Jets -- 4.2 Injection, Mixing and Combustion Under Real-Gas Conditions -- 4.3 Boundary Layer Heat Transfer Modelling -- 4.4 Combustion Stability of Rocket Engines -- 5 Research Area D: Thrust Nozzle -- 5.1 Thermal Barrier Coatings and Component Life Prediction -- 5.2 Cooling Channel Flows -- 5.3 Fluid Structure Interaction -- 6 Research Area K: Thrust-Chamber Assembly -- 6.1 Combustion and Heat Transfer -- 6.2 Dual Bell Nozzle -- 6.3 Thrust-Chamber Demonstrators -- 7 Central Research and Education Support -- References -- Structural Cooling -- A Coupled Two-Domain Approach for Transpiration Cooling -- 1 Motivation -- 2 Mathematical Modeling -- 2.1 Hot Gas Domain -- 2.2 Porous Medium Domain -- 2.3 Coupling Conditions -- 3 Numerical Methods -- 4 Numerical Results -- 4.1 Non-uniform Injection into a Subsonic Hot Gas Channel Flow -- 4.2 Uniform Injection into a Supersonic Nozzle Flow -- 5 Conclusion -- References -- Innovative Cooling for Rocket Combustion Chambers -- 1 Introduction -- 2 Experimental Setup -- 2.1 Stacked Transpiration Cooling Specimen -- 2.2 Hot Gas Channel and Measurement Setup -- 3 Numerical Setup -- 4 Results and Interpretation of the Serial Transpiration Cooling Experiment -- 5 Summary and Outlook -- References -- Film Cooling in Rocket Nozzles -- 1 Motivation -- 2 Film Cooling Theory -- 2.1 Film Cooling Efficiency , 2.2 Film Cooling Model -- 3 Experimental Setup -- 3.1 Test Facility -- 4 Results Conical Nozzle -- 4.1 Reference Flow -- 4.2 Parametric Study -- 4.3 Correlation -- 5 Results Dual-Bell Nozzle -- 5.1 Experiments Without Film Cooling -- 5.2 Experiments with Film Cooling -- 6 Conclusion -- References -- Numerical Simulation of Film Cooling in Supersonic Flow -- 1 Introduction -- 2 Flow Configuration -- 2.1 Film Cooling -- 3 Numerical Method -- 4 Results -- 4.1 Influence of Coolant Mass Flow Rate -- 4.2 Influence of Coolant Mach Number -- 4.3 Influence of the Upstream Wall Temperature -- 4.4 Lip-Thickness Influence -- 4.5 Influence of the Coolant Velocity Profile -- 4.6 Correlation of Data -- 5 Conclusions and Outlook -- References -- Heat Transfer in Pulsating Flow and Its Impact on Temperature Distribution and Damping Performance of Acoustic Resonators -- 1 Introduction and Placement in SFB -- 2 Impact of Temperature Inhomogeneities on Damping Performance -- 3 Impact of Acoustic Oscillations on Heat Transfer -- 3.1 Wall Normal Heat Transfer -- 3.2 Longitudinal Heat Transfer -- 4 Summary and Conclusions -- References -- Aft-Body Flows -- Effects of a Launcher's External Flow on a Dual-Bell Nozzle Flow -- 1 Introduction -- 2 Experimental Setup -- 2.1 BFS Model -- 2.2 Measurement Techniques -- 3 Results -- 3.1 Steady-State Sea Level Mode -- 3.2 Steady-State Altitude Mode -- 3.3 Transition -- 4 Summary and Conclusions -- References -- Interaction of Wake and Propulsive Jet Flow of a Generic Space Launcher -- 1 Introduction -- 2 Experimental and Numerical Setup -- 2.1 Geometry and Test Cases -- 2.2 Experimental Setup -- 2.3 Numerical Setup -- 3 Results -- 3.1 Passive Flow Control on TIC Configuration -- 3.2 Analysis of Dual-Bell Transition-Effect of Reynolds Number -- 3.3 Analysis of Dual-Bell Transition-Influence of Afterbody Geometry -- 4 Summary , 2.2 Load Conditions -- 2.3 Load Phases -- 2.4 Deformations and Lifetime -- 3 Cooling Channel Measurements -- 3.1 Test Setup -- 3.2 Light Sheet Alignment -- 3.3 Window Size Analysis -- 3.4 Particle Shift -- 4 Conclusions -- References -- Mechanical Integrity of Thermal Barrier Coatings: Coating Development and Micromechanics -- 1 Introduction -- 2 Methods -- 2.1 Coating Process -- 2.2 Arc Heated Hypersonic Wind Tunnel -- 2.3 Subscale Combustion Chamber -- 3 Coating Design for a Large Scale Combustion Chamber -- 3.1 Mechanical Loads -- 3.2 Crack Propagation -- 4 Validation Tests -- 4.1 Arc Heated Hypersonic Wind Tunnel -- 4.2 Subscale Combustion Chamber -- 5 Conclusions -- References -- Assessment of RANS Turbulence Models for Straight Cooling Ducts: Secondary Flow and Strong Property Variation Effects -- 1 Introduction -- 2 High Aspect Ratio Cooling Duct -- 2.1 Equation System and Numerical Model -- 2.2 Simulation Setup -- 2.3 Flow and Temperature Field -- 3 Channel Flow with Strong Property Variations -- 3.1 Equation System and Numerical Model -- 3.2 Simulation Setup -- 3.3 Flow and Temperature Field -- 4 Summary and Conclusion -- References -- Experiments on Aerothermal Supersonic Fluid-Structure Interaction -- 1 Introduction -- 1.1 FSI and SWBLI -- 1.2 High Temperature FSI -- 2 Experiments on Aerothermoelastic FSI with SWBLI -- 2.1 Wind Tunnel H2K -- 2.2 Wind Tunnel Model and Instrumentation -- 2.3 Properties of the Elastic Panel -- 2.4 Experimental Results -- 3 Experiments on High Temperature FSI with Plastic Deformation -- 3.1 Arc-Heated Wind Tunnel L3K -- 3.2 Wind Tunnel Model and Instrumentation -- 3.3 Experimental Results -- 4 Conclusion -- References -- Numerical Modelling of Fluid-Structure Interaction for Thermal Buckling in Hypersonic Flow -- 1 Introduction -- 2 Fluid-Structure Interaction -- 3 Structural Model -- 3.1 Thermal Analysis , 3.2 Structural Analysis , Large-Eddy Simulations for the Wall Heat Flux Prediction of a Film-Cooled Single-Element Combustion Chamber -- 1 Introduction -- 2 Governing Equations and Numerical Procedure -- 3 Test Case -- 3.1 Combustion Chamber Test Cases -- 3.2 Roughness Test Cases -- 4 Results -- 4.1 Combustion Chamber Results -- 4.2 Roughness Results -- 5 Conclusions -- References -- Calculation of the Thermoacoustic Stability of a Main Stage Thrust Chamber Demonstrator -- 1 Introduction -- 2 Test Case -- 3 Stability Assessment Procedure -- 3.1 Perturbation Analysis -- 3.2 Mean Flow -- 3.3 Flame Response -- 3.4 External Components and Design Adaption -- 4 Numerical Setup -- 4.1 Eigensolution Study -- 4.2 Single Flame -- 5 Results -- 5.1 Dome Acoustics -- 5.2 Coupled Acoustics -- 5.3 Stability Behavior -- 6 Conclusions -- References -- Experimental Investigation of Injection-Coupled High-Frequency Combustion Instabilities -- 1 Introduction -- 1.1 Summary of Previous Investigations -- 2 Experimental Technique -- 2.1 Experimental Setup -- 2.2 Methodology -- 3 Results and Discussion -- 3.1 Mean Flame Images -- 3.2 Dynamic Characteristics -- 3.3 LOX Core Dynamic Response to Excited Injector Eigenmodes -- 3.4 Damping Device to Reduce Risk of Injection-Coupled Instabilities -- 4 Summary and Conclusions -- References -- Thrust Nozzle -- Pseudo-transient 3D Conjugate Heat Transfer Simulation and Lifetime Prediction of a Rocket Combustion Chamber -- 1 Introduction -- 2 Conjugate Heat Transfer Simulation -- 2.1 Computational Model -- 2.2 Results and Validation -- 3 Lifetime Prediction -- 3.1 Transient Thermal Analysis -- 3.2 Quasi-static Mechanical Analysis -- 4 Conclusion -- References -- Lifetime Experiments of Regeneratively Cooled Rocket Combustion Chambers and PIV Measurements in a High Aspect Ratio Cooling Duct -- 1 Introduction -- 2 Fatigue Experiment -- 2.1 Experimental Set-Up , References -- Rocket Wake Flow Interaction Testing in the Hot Plume Testing Facility (HPTF) Cologne -- 1 Introduction -- 2 The Hot Plume Testing Facility (HPTF) -- 2.1 Vertical Wind Tunnel Cologne (VMK) -- 2.2 GH2/GO2 Supply Facility -- 3 Characterization of HPTF for Wind Tunnel Testing -- 3.1 HPTF Characterization Test Setup -- 3.2 HPTF Characterization Test Results -- 4 Cold and Hot Plume Interaction Testing -- 4.1 GH2/GO2 Wind Tunnel Model -- 4.2 Test Program and Test Conditions -- 4.3 Wind Tunnel Test Results -- 5 Conclusions -- References -- Numerical Analysis of the Turbulent Wake for a Generic Space Launcher with a Dual-Bell Nozzle -- 1 Introduction -- 2 Computational Approach -- 2.1 Geometry and Flow Conditions -- 2.2 Zonal RANS/LES Flow Solver -- 2.3 Computational Mesh -- 3 Results -- 3.1 Supersonic Configuration -- 3.2 Transonic Configuration -- 4 Conclusions -- References -- Numerical Investigation of Space Launch Vehicle Base Flows with Hot Plumes -- 1 Introduction -- 2 Numerical Method and Setup -- 3 Results of Thermal Flow Structure Coupling -- 4 Investigation of Aft-Body Flow Fields -- 5 Conclusions and Outlook -- References -- Combustion Chamber -- On the Consideration of Diffusive Fluxes Within High-Pressure Injections -- 1 Introduction -- 2 Phenomenological Considerations on Mixing Jets -- 3 Numerical Consideration and Thermodynamic Modeling -- 3.1 Thermodynamic Modeling -- 4 Numerical Results: LES of N-Hexane/Nitrogen Jet -- 5 Conclusions -- References -- Numerical Investigation of Injection, Mixing and Combustion in Rocket Engines Under High-Pressure Conditions -- 1 Introduction -- 2 Physical and Mathematical Modeling -- 2.1 Governing Equations -- 2.2 Numerical Flow Solver -- 2.3 Thermodynamic Modeling -- 2.4 Combustion Modeling -- 3 Results and Discussion -- 3.1 Thermodynamics -- 3.2 Combustion -- 4 Conclusion -- References

Additional Edition: Print version Adams, Nikolaus A. Future Space-Transport-System Components under High Thermal and Mechanical Loads Cham : Springer International Publishing AG,c2020 ISBN 9783030538460

Language: English

Keywords: Electronic books.

URL: FULL  ((Currently Only Available on Campus))