Vibro-accoustical instabilities induced by combustion dynamics in gas turbine combustors

Pozarlik, Artur Krzysztof

doi:10.3990/1.9789036531269

Cited by 14 publications

(22 citation statements)

References 47 publications

(69 reference statements)

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“…However, earlier performed analyses on different types of noise sources in the combustor chamber showed that the acoustic noise induced by the unsteady combustion process is the strongest acoustic source [19]. The acoustic phenomenon in a gas turbine combustor can originate from different sources.…”

Section: -D(ç)_mentioning

confidence: 99%

Sensitivity of the Numerical Prediction of Turbulent Combustion Dynamics in the LIMOUSINE Combustor

Shahi¹,

Kok²,

Pozarlik³

et al. 2013

Journal of Engineering for Gas Turbines and Power

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The objective of this study is to investigate the sensitivity and accuracy of the reaction flow-field prediction for the LIMOUSINE combustor with regard to choices in computational mesh and turbulent combustion model. The UMOUSINE combustor is a partially premixed, bluff body-stabilized natural gas combustor designed to operate at 40-80 kW and atmospheric pressure and used to study combustion instabilities. The transient simulation of a turbulent combusting flow with the purpose to study thermoacoustic instabilities is a very time-consuming process. Eor that reason, the meshing approach leading to accurate numerical prediction, known sensitivity, and minimized amount of mesh elements is important. Since the numerical dissipation (and dispersion) is highly dependent on, and affected by, the geometrical mesh quality, it is of high importance to control the mesh distribution and element size across the computational domain. Typically, the structural mesh topology allows using much fewer grid elements compared to the unstructured grid; however, an unstructured mesh is favorable for flows in complex geometries. To explore computational stability and accuracy, the numerical dissipation of the cold flow with mixing of fuel and air is studied first in the absence of the combustion process. Thereafter, the studies are extended to combustible flows using standard available ANSYS-CFX combustion models. To validate the predicted variable fields of the combustor's transient reactive flows, the numerical results for dynamic pressure and temperature variations, resolved under structured and unstructured mesh conditions, are compared with experimental data. The obtained results show minor dependence on the used mesh in the velocity and pressure profiles of the investigated grids under nonreacting conditions. More significant differences are observed in the mi.xing behavior of air and fuel flows. Here, the numerical dissipation of the (unstructured) tetrahedral mesh topology is higher than in the case of the (structured) hexahedral mesh. For that reason, the combusting flow, resolved with the use of the hexahedral mesh, presents better agreement with experimental data and demands less computational effort. Finally, in the paper, the performance of the combustion model for reacting flow is presented and the main issues of the applied combustion modeling are reviewed.

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Section: -D(ç)_mentioning

confidence: 99%

Sensitivity of the Numerical Prediction of Turbulent Combustion Dynamics in the LIMOUSINE Combustor

Shahi¹,

Kok²,

Pozarlik³

et al. 2013

Journal of Engineering for Gas Turbines and Power

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“…Prakash [2] studied the dynamic performances of chamber flame at different gas equivalent ratios, and the interaction between acoustic pressure and flame was analysed. Artur [3] analysed the heat-acoustic instability, and the interaction between temperature field and acoustic pressure field was studied. Huls [4] studied the vibration in combustion chambers basing on acoustic-elastic finite element model and sound vibration test.…”

Section: Introductionmentioning

confidence: 99%

Study on Thermal-acoustic-structural Performance of Aeroengine Combustor Based on Coupled-Field Technology

Guan¹,

Ai²

2019

Proceedings of Global Power &Amp; Propulsion Society

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A typical combustion chamber model is established to study the thermal-acoustic-structural performance of Aeroengine Combustor. Fluid and structure interaction (FSI) technology is used to simulate the ignition process of combustion chamber with different air-fuel ratio and vibration of combustion chamber. The calculated data is exchanged between fluid and solid interface by two-way coupled FSI. The results show that by varying the air-fuel ratio from 0.6 to 1.4, the average temperature and acoustic pressure are increased by 15% and 64.8%, respectively. The stress waves of the combustion chamber are consisted with three main frequencies of waves, which are one, two, and three doubling frequency, respectively. The studied structural vibrations are mainly caused by the one and three doubling frequency. The structural deformation caused by acoustic pressure accounts for 3.3%-4.9% larger than that of thermal expansion.

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“…If these acoustic oscillations modify the burning rate with the correct phasing, the intensity of the instabilities will be increased, causing amplified flame oscillations. This then causes larger amplitude acoustic disturbances to be produced from the unsteady heat release oscillations, which will drive instability growth [1,2,3].…”

Section: Introductionmentioning

confidence: 99%

Investigation of a Single Injector with Applied High Frequency Pressure Disturbances For Applications To Liquid Rocket Engine Combustion Instabilities

Bennewitz

Lineberry

Frederick

2013

49th AIAA/ASME/SAE/ASEE Joint Propulsion Conference

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This research investigation demonstrates a new high frequency combustion instability control approach in which the dominant instability mode is able to be suppressed by strategically applying pressure disturbances within the oxidizer post of an injector. By housing a piezoelectric speaker at the base of the injector, the incoming oxidizer flow into the combustor is able to be acoustically modulated, causing the oscillatory behavior of the combustor to be altered. Thus, given the correct acoustic signal, a suppression of high frequency combustion instabilities is able to be achieved. To test this concept, a cylindrical model combustor (dinner = 4 in. and l = 6.5 in.) was constructed, which incorporated a single 45 o impinging pentad injector with a JBL 2446J Compression Driver at the base of the oxidizer post. Using this test facility, an investigation involving the application of varying bands of white noise (ranging from 0 Hz -500 Hz to 2,000 Hz -2,500 Hz) to dampen out a high frequency instability (f ≈ 2,430 Hz) was conducted. Across the two tests performed, it was found that a complete suppression of the f ≈ 2,430 Hz instability was possible when applying ≈ 500 Hz -1000 Hz band limited white noise at 0.3 psi rms constant amplitude. Thus, this indicates that strategically applying band limited white noise within an injector through acoustic forcing could potentially be used to control high frequency combustion instabilities within liquid rocket engine combustors.

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Vibro-accoustical instabilities induced by combustion dynamics in gas turbine combustors

Cited by 14 publications

References 47 publications

Sensitivity of the Numerical Prediction of Turbulent Combustion Dynamics in the LIMOUSINE Combustor

Sensitivity of the Numerical Prediction of Turbulent Combustion Dynamics in the LIMOUSINE Combustor

Study on Thermal-acoustic-structural Performance of Aeroengine Combustor Based on Coupled-Field Technology

Investigation of a Single Injector with Applied High Frequency Pressure Disturbances For Applications To Liquid Rocket Engine Combustion Instabilities

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