Combustion Stability Analysis using Feedback Transfer Function

Kim, Jina; Yoon, Myung Gon; Kim, Deasik

doi:10.15231/jksc.2016.21.3.024

Cited by 8 publications

(2 citation statements)

References 10 publications

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“…The facility consists of a swirl injector, a quartz combustor and a steel combustor with a movable plug nozzle. More information can be checked in the previous study and will not be described in detail here [12][13][14]. The schematic diagram of a model chamber is shown in Fig.…”

Section: Methodsmentioning

confidence: 99%

Combustion Instability Analysis of a Model Gas Turbine by Application of Dynamic Mode Decomposition

Wang¹,

Son²,

Sohn³

et al. 2019

jksc

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Dynamic mode decomposition (DMD) technique is applied to analyze combustion instabilities in a model gas turbine combustor. The flame transfer function (FTF) obtained by the DMD method agrees with the experimental results qualitatively. However, FTF results show that the perturbation frequency with the largest gain is 100Hz, which contradicts the 1000Hz with the largest amplitude in the fast Fourier transform (FFT) results. In order to figure out this, gains and damping coefficients of all resonance frequencies are calculated by DMD technique. Results show the possibility that the model combustor has high-frequency instabilities as a results of coupling between flame and chamber responses. Another finding is that to obtain a pure FTF, the combustor must be removed to exclude coupling of chamber response with flame response.

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Section: Methodsmentioning

confidence: 99%

Combustion Instability Analysis of a Model Gas Turbine by Application of Dynamic Mode Decomposition

Wang¹,

Son²,

Sohn³

et al. 2019

jksc

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show abstract

“…Two popular methods for thermoacoustic combustion instability prediction are based on RANS and LES analyses (for example, see [49][50][51][52][53]). The methods rely on a CFD solver to find the statistics or unsteady motions of the combustion chamber or entire engine interior.…”

Section: Applicationsmentioning

confidence: 99%

Analytical Equations for Thermoacoustic Instability Sources and Acoustic Radiation from Reacting Turbulence

Miller

2020

International Journal of Aerospace Engineering

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We seek to ascertain and understand source terms that drive thermoacoustic instability and acoustic radiation. We present a new theory based on the decomposition of the Navier-Stokes equations coupled with the mass fraction equations. A series of solutions are presented via the method of the vector Green’s function. We identify both combustion-combustion and combustion-aerodynamic interaction source terms. Both classical combustion noise theory and classical Rayleigh criterion are recovered from the presently developed more general theory. An analytical spectral prediction method is presented, and the two-point source terms are consistent with Lord Rayleigh’s instability model. Particular correlations correspond to the source terms of Lighthill, which represent the noise from turbulence and additional terms for the noise from reacting flow.

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Prediction of combustion instability by combining transfer functions in a model rocket combustor

Wang

Sohn

Bae

et al. 2021

Aerospace Science and Technology

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Combustion Stability Analysis using Feedback Transfer Function

Cited by 8 publications

References 10 publications

Combustion Instability Analysis of a Model Gas Turbine by Application of Dynamic Mode Decomposition

Combustion Instability Analysis of a Model Gas Turbine by Application of Dynamic Mode Decomposition

Analytical Equations for Thermoacoustic Instability Sources and Acoustic Radiation from Reacting Turbulence

Prediction of combustion instability by combining transfer functions in a model rocket combustor

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