Thermoacoustic response of fully compressible counterflow diffusion flames to acoustic perturbations |
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| Institution: | 1. Department of Mechanical and Civil Engineering, California Institute of Technology, Pasadena, USA;2. Department of Mechanical and Mechatronics Engineering, University of Waterloo, Waterloo, Ontario, Canada;1. Technical University of Darmstadt, Department of Mechanical Engineering, Reactive Flows and Diagnostics, Otto-Berndt-Str. 3, Darmstadt 64287, Germany;2. Barlow Combustion Research, Livermore, USA;1. Key laboratory for Thermal Science and Power Engineering of Ministry of Education, Department of Energy and Power Engineering, Tsinghua University, Beijing 100084, PR China;2. Lab of Space Propulsion Technology, Beijing Institute of Control Engineering, Beijing 100190, PR China;3. Institute of Electrical Engineering, Chinese Academy of Sciences, Beijing 100190, PR China;4. School of Aerospace Engineering, Beijing Institute of Technology, Beijing 100081, PR China;1. Steinbuch Centre for Computing, Karlsruhe Institute of Technology Hermann-von-Helmholtz-Platz 1, 76344 Eggenstein-Leopoldshafen, Germany;2. Engler-Bunte-Institute, Division of Combustion Technology, Karlsruhe Institute of Technology, Engler-Bunte-Ring 1, 76131 Karlsruhe, Germany;3. Department of Mechanical Engineering, Stanford University, Stanford CA 94305, USA;1. Instituto Nacional de Técnica Aeroespacial, Madrid 28850, Spain;2. Universidad Carlos III de Madrid, Av. de la Universidad 30, Leganés (Madrid), 28911, Spain;1. State Key Laboratory of Clean Energy Utilization, Zhejiang University, Hangzhou 310027, China;2. School of Aeronautics and Astronautics, Zhejiang University, Hangzhou 310027, China;3. Department of Mechanical Engineering and Science, Kyoto University, Kyoto 615–8540, Japan;4. College of Mechanical Engineering, Zhejiang University of Technology, Hangzhou 310023, China |
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| Abstract: | The goal of this research is to study the thermoacoustic response of diffusion flames due to their relevance in applications such as rocket engines. An in-house code is extended to solve the fully compressible counterflow diffusion flame equations, allowing for a spatially- and temporally-varying pressure field. Various hydrogen-air flames with a range of strain rates are simulated using detailed chemistry. After introducing sinusoidal pressure perturbations at the inlet, the gain and phase of various quantities of interest are extracted. As the frequency is increased, the gain of the temperature source term transitions from the perturbed steady flamelet value to a first plateau at intermediate frequencies, and finally to a second plateau at the highest frequencies. At these high frequencies, the gain of the integrated heat release decays to zero, underscoring the importance of compressibility. These three regimes can be identified and explained through a linearization and frequency domain analysis of the governing equations. The validity of the low Mach number assumption and importance of detailed chemistry are assessed. |
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