Numerical simulation of oxy-fuel combustion for gas turbine applications

Krieger, G.; Campos, André P. V. de; Takehara, Marcelo Dal Belo; Cunha, Fábio Alfaia da; Veras, Carlos

doi:10.1016/j.applthermaleng.2015.01.001

Cited by 49 publications

(15 citation statements)

References 22 publications

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“…The inlet turbulent intensity and hydraulic diameter for fuel were set to 5% and 10 mm respectively. The value of turbulent intensity is based on the value as suggested in [31]. The combustor wall was set to no-slip boundary and no-species flux condition.…”

Section: Boundary Conditionsmentioning

confidence: 99%

Experimental and numerical studies on the premixed syngas swirl flames in a model combustor

Samiran

Chong

et al. 2019

International Journal of Hydrogen Energy

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Experimental and numerical investigations were performed to study the combustion characteristics of synthesis gas (syngas) under premixed swirling flame mode. Four different type of syngases, ranging from low to high H 2 content were tested and simulated. The global flame structures and post emission results were obtained from experimental work, providing the basis of validation for simulations using flamelet generated manifold (FGM) modelling approach via a commercial computational fluid dynamic software. The FGM method was shown to provide reasonable agreement with experimental result, in particular the post-exhaust emissions and global flame shapes. Subsequently, the FGM method was adopted to model the flame structure and predict the radical species in the reaction zones. Simulation result shows that H 2enriched syngas has lower peak flame temperature with lesser NO species formed in the reaction zone.

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Section: Boundary Conditionsmentioning

confidence: 99%

Experimental and numerical studies on the premixed syngas swirl flames in a model combustor

Samiran

Chong

et al. 2019

International Journal of Hydrogen Energy

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“…Besides, the use of LES requires huge computational power and is unaffordable for most industrial problems. On the other hand, the far less computational power required Reynolds average Navier-Stoke (RANS) method fails to predict the reacting flow in realistic gas turbine combustors accurately [10]. The principle cause is attributed to the use of the unsuitable non-premixed combustion model rather than the problem of widely used RANS models.…”

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confidence: 99%

Comparative study of non-premixed and partially-premixed combustion simulations in a realistic Tay model combustor

Zhang

Ghobadian

Nouri

2017

Applied Thermal Engineering

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A comparative study of two combustion models based on non-premixed assumption and partially premixed assumptions using the overall models of Zimont Turbulent Flame Speed Closure Method (ZTFSC) and Extended Coherent Flamelet Method (ECFM) are conducted through Reynolds stress turbulence modelling of Tay model gas turbine combustor for the first time. The Tay model combustor retains all essential features of a realistic gas turbine combustor. It is seen that the non-premixed combustion model fails to predict the combustion completely due to an incorrect assumption of diffusion flame scenario invoking infinitely fast chemistry in complicated flow environments while the two partially premixed combustion models accurately predict the flame pattern in the primary region of the combustor. The ZTFSC model outperformed the ECFM model by producing a better temperature agreement with the experimental result. The latter model predicts lower temperature due to the underestimation of reaction progress. Additionally, a cross-comparison of the present RSM prediction invoking ZTFSC model with LES prediction reported in the literature is conducted. The former produces more accurate species concentration and flame pattern than the latter. This is mainly due to the incorrect assumption of nonpremixed combustion used in LES prediction reported in the literature. It is interesting to find that when nonpremixed combustion model is used for both RSM and LES predictions, the LES predicts higher temperature closer to the injection nozzle of combustor than the RSM model, though the flame shape in both cases is incorrect. This is mainly due to the fact that the traditional RANS model dissipates the energy of swirling flow too fast in the primary region of the combustor. The weaker centre recirculation zone (CRZ) created by vortex breakdown recirculate less air to the area near the injection nozzle resulting in fuel rich combustion. It indicates that the temperature difference between predicted results using RSM in conjunction with ZTFC model and experimental results can be improved by using less energy dissipating turbulence models such as scale resolving simulation (SRS). 1. Introduction The advent of Gas-Turbine for military purposes tracks back to 1940s, and it is subsequently used for aviation and later for ground level power [1]. The main challenge of aviation industries nowadays is the efficiency, stability of combustion and pollutant control, such as the emission of carbon dioxide (CO2), nitrogen oxide, sulphur dioxide and etc. In order to design combustors with desired features and meet with relevant criteria, improved understanding of turbulent combustion through both realistic experimental observation and numerical simulation and validation is required. The former alone is expensive for industries before a more cost-effective numerical prediction is performed. However, the accuracy of the numerical simulation is doubtful as it is highly dependent on the turbulence and combustion models, i.e. the mixing and chemical reactions. To i...

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“…The depletion of energy resources and growth of environmental pollution are critical concerns at the turn of the 21st century [1][2][3]. As emission regulations become more stringent in efforts to suppress pollution, many researchers are working on developing a new type of power plant which produces significantly lower emissions: an advanced gas turbine.…”

Section: Research Motivationmentioning

confidence: 99%

A Real-Time Combustion Instability Simulation with Comprehensive Thermo-Acoustic Dynamic Model

et al. 2018

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The thermo-acoustic instability in the combustion process of a gas turbine is caused by the interaction of the heat release mechanism and the pressure perturbation. These acoustic vibrations cause fatigue failure of the combustor and decrease the combustion efficiency. This study aims to develop a segmented dynamic thermo-acoustic model to understand combustion instability of a gas turbine. Then, the combustion instability was designed using the acoustic heat release model, and the designed instability model was segmented using the finite difference method, to evaluate the characteristics of flame propagation at each node. The combustion instability model was validated using experimental data to verify the instability amplitude. Also, the optimal node number was determined using the adiabatic flame temperature response. 10 nodes were selected in this study. A sensitivity analysis showed the predicted instability amplitude decreased when the nodes increased until node 4, due to heat generation. However, above 4 nodes the amplitude decreased, since the combustion outlet was directly connected to the ambient. As a result, the segmented combustion instability model was able to evaluate the flame propagation characteristics more accurately and found the largest area of instability was near the flame area.

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Numerical simulation of oxy-fuel combustion for gas turbine applications

Cited by 49 publications

References 22 publications

Experimental and numerical studies on the premixed syngas swirl flames in a model combustor

Experimental and numerical studies on the premixed syngas swirl flames in a model combustor

Comparative study of non-premixed and partially-premixed combustion simulations in a realistic Tay model combustor

A Real-Time Combustion Instability Simulation with Comprehensive Thermo-Acoustic Dynamic Model

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