Acoustic Instabilities in a Taylor-Couette Combustor PDF Download
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Author: Nicholas Joseph Killingsworth
Publisher:
ISBN:
Category :
Languages : en
Pages : 140
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Book Description
Author: Nicholas Joseph Killingsworth
Publisher:
ISBN:
Category :
Languages : en
Pages : 140
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Book Description
Author: Ayo Oyediran
Publisher:
ISBN:
Category :
Languages : en
Pages : 16
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Book Description
Author: Dan Zhao
Publisher: Academic Press
ISBN: 0323899188
Category : Technology & Engineering
Languages : en
Pages : 1145
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Book Description
Thermoacoustic Combustion Instability Control: Engineering Applications and Computer Codes provides a unique opportunity for researchers, students and engineers to access recent developments from technical, theoretical and engineering perspectives. The book is a compendium of the most recent advances in theoretical and computational modeling and the thermoacoustic instability phenomena associated with multi-dimensional computing methods and recent developments in signal-processing techniques. These include, but are not restricted to a real-time observer, proper orthogonal decomposition (POD), dynamic mode decomposition, Galerkin expansion, empirical mode decomposition, the Lattice Boltzmann method, and associated numerical and analytical approaches. The fundamental physics of thermoacoustic instability occurs in both macro- and micro-scale combustors. Practical methods for alleviating common problems are presented in the book with an analytical approach to arm readers with the tools they need to apply in their own industrial or research setting. Readers will benefit from practicing the worked examples and the training provided on computer coding for combustion technology to achieve useful results and simulations that advance their knowledge and research. Focuses on applications of theoretical and numerical modes with computer codes relevant to combustion technology Includes the most recent modeling and analytical developments motivated by empirical experimental observations in a highly visual way Provides self-contained chapters that include a comprehensive, introductory section that ensures any readers new to this topic are equipped with required technical terms
Author: Sandeep Ravikumar Murthy
Publisher:
ISBN:
Category :
Languages : en
Pages :
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Author:
Publisher:
ISBN:
Category :
Languages : en
Pages : 18
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Author: Vahid Vaezi
Publisher:
ISBN:
Category :
Languages : en
Pages : 310
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Author: K. Molavi
Publisher:
ISBN:
Category :
Languages : en
Pages :
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Author: Christian O. Paschereit
Publisher:
ISBN:
Category :
Languages : en
Pages :
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Author: Lutz Blätte
Publisher:
ISBN:
Category :
Languages : en
Pages : 154
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Book Description
Most combustion machines feature internal flows with very high energy densities. If a small fraction of the total energy contained in the flow is diverted into oscillations, large mechanical or thermal loads on the structure can be the result, which are potentially devastating if not predicted correctly. This is particularly the case for lightweight high performing devices like rockets. The problem is commonly known as "Combustion Instability". Several mechanisms have been identied in the past that link the flow field to the acoustics inside a combustion chamber and thereby drive or dampen oscillations, one of them being vortex shedding. The interaction between the highly sheared flow behind an obstacle and longitudinal acoustic oscillations inside a solid rocket booster is investigated both analytically and experimentally. The analytical approach is developed based on modeling of the second order acoustic energy. The energy model is applied to the specic flow conditions just downstream of a single baffle protruding into the flow. The mean flow profile is assumed to be of the form of a hyperbolic tangent, the unsteady acoustic velocities are assumed to be sinusoidally oscillating. Solutions for the unsteady rotational velocities and the unsteady vorticity are derived. The resulting flow field is utilized in stability calculations for a simplified two-dimensional axial-symmetric geometry. This yields to linear growth rates of the (longitudinal) oscillation modes. The growth rates are functions of the chamber geometry, the mean ow properties and the properties of the shear layer created by the flow restriction. A cold flow experiment is designed, tested and performed in order to validate the analytical findings. Flow is injected radially into a tube with acoustic closed-closed end conditions. A single baffle is installed in the tube, the axial position of the baffle is varied as well as its inner diameter. Frequency spectra of pressure oscillations are recorded. The experimental data is then compared qualitatively to the analytical growth rates. Those longitudinal Normal Modes, which feature the highest theoretical growth rates, are expected to be most prominent in the experimental data. This behavior is clearly observable.
Author: Carl L. Oberg
Publisher:
ISBN:
Category : Combustion
Languages : en
Pages : 187
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Book Description
Acoustic instability in solid propellant rockets is observed as a high-amplitude oscillation in the acoustic modes of the gas cavity, the combustion processes providing the driving energy. In general, the solid phase, i.e., the propellant, participates in the wave behavior. In this work, the behavior of both the gas phase and the solid phase were experimentally studied in a side-vented end burner. When the burner was operated with a grain in only one end, a difference in acoustic pressure amplitudes not previously reported was observed. The phenomenon was confirmed and studied in some detail. It does not affect the data used to calculate acoustic admittance values.
