CFD Modeling of Flame Structures in a Gas Turbine Combustion Reactor: Velocity, Temperature, and Species Distribution

Bahramian, Alireza; Maleki, Mozhdeh; Medi, Bijan

doi:10.1515/ijcre-2016-0076

Cited by 5 publications

(2 citation statements)

References 33 publications

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“…A laboratory scale tubular combustion chamber is modeled, and CFD combustion simulation was performed with two different mechanisms, namely, Eddy Dissipation Concept (EDC) and Finite Rate/Eddy Dissipation (FR-ED) using methane as fuel (Bahramian et al, 2017). The results of the two approaches are compared.…”

Section: Combustor Design Methodsmentioning

confidence: 99%

Combustion chamber design and reaction modeling for aero turbo-shaft engine

Marudhappan

Chandrasekhar

Reddy

2018

AEAT

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Purpose The purpose of this paper is to formulate a structured approach to design an annular diffusion flame combustion chamber for use in the development of a 1,400 kW range aero turbo shaft engine. The purpose is extended to perform numerical combustion modeling by solving transient Favre Averaged Navier Stokes equations using realizable two equation k-e turbulence model and Discrete Ordinate radiation model. The presumed shape β-Probability Density Function (β-PDF) is used for turbulence chemistry interaction. The experiments are conducted on the real engine to validate the combustion chamber performance. Design/methodology/approach The combustor geometry is designed using the reference area method and semi-empirical correlations. The three dimensional combustor model is made using a commercial software. The numerical modeling of the combustion process is performed by following Eulerian approach. The functional testing of combustor was conducted to evaluate the performance. Findings The results obtained by the numerical modeling provide a detailed understanding of the combustor internal flow dynamics. The transient flame structures and streamline plots are presented. The velocity profiles obtained at different locations along the combustor by numerical modeling mostly go in-line with the previously published research works. The combustor exit temperature obtained by numerical modeling and experiment are found to be within the acceptable limit. These results form the basis of understanding the design procedure and opens-up avenues for further developments. Research limitations/implications Internal flow and combustion dynamics obtained from numerical simulation are not experimented owing to non-availability of adequate research facilities. Practical implications This study contributes toward the understanding of basic procedures and firsthand experience in the design aspects of combustors for aero-engine applications. This work also highlights one of the efficient, faster and economical aero gas turbine annular diffusion flame combustion chamber design and development. Originality/value The main novelty in this work is the incorporation of scoops in the dilution zone of the numerical model of combustion chamber to augment the effectiveness of cooling of combustion products to obtain the desired combustor exit temperature. The use of polyhedral cells for computational domain discretization in combustion modeling for aero engine application helps in achieving faster convergence and reliable predictions. The methodology and procedures presented in this work provide a basic understanding of the design aspects to the beginners working in the gas turbine combustors particularly meant for turbo shaft engines applications.

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Section: Combustor Design Methodsmentioning

confidence: 99%

Combustion chamber design and reaction modeling for aero turbo-shaft engine

Marudhappan

Chandrasekhar

Reddy

2018

AEAT

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“…This increase in the mass of the nitrogen resulted in the blockage of the swirl flow and there by reducing the size of the recirculation zone.They showed that the conversion of bubble and helix type vortex breakdown are related directly with the swirl number. Bahramian et al [26] simulated a premixed combustor in 2-D and 3-D using EDC and finite-rate/eddy-dissipation model. EDC model predicted an increase in velocity at the nozzle exit and exhaust zones.…”

Section: Premixed Combustionmentioning

confidence: 99%

Effects of Swirl Number and Central Rod on Flow in a Lean Premixed Swirl Combustor

Yellugari,

Villalva Gomez,

Gutmark

2023

Combustion Science and Technology

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Gas turbine combustors are used to extract chemical energy from the combustion of fuel in presence of an oxidizer to power turbines. Environmental concerns provide motivation to develop more efficient and less polluting gas turbine engines. To achieve good emission performance, lean burn combustors with low pollutant emissions have been developed. These combustors operate at fuel lean conditions and they can be classified into lean premixed and pre-vaporized (LPP) combustor, where the fuel and oxidizer are premixed and pre-vaporized to form a homogeneous mixture in a dedicated region, premixer, just before the fuel-oxidizer mixture enters the combustion chamber, and lean direct injection (LDI) combustor, where the fuel is directly injected into the flame zone without any premixing with oxidizer [1]. The premixing and pre-vaporizing reduce the residence time, the amount of time the gases are in the combustion chamber. The reduction in residence time reduces the NO x emissions, as the high NO x emissions are produced with a long residence time in the combustion chamber.The flow behavior of non-reacting and reacting flow in a lean premixed swirl combustor, adapted from KAUST experimental rig, has been studied using RANS in the commercial software, Ansys -Fluent. Turbulence is modeled using the two equation realizable k − model and the turbulence -chemistry interaction is modeled by a flamelet generated manifold (FGM) technique. At first, non-reacting flow was simulated in lean premixed swirl combustor. These simulation results were compared to the experiments done by Sabatino et al. [2] and LES work of Maestro et al. [3]. This non-reacting flow solution was used as an initial condition to the reacting flow for a faster convergence of the solution, with methane-air mixture at an equivalence ratio of 0.67. GRI 3.0 mechanism was used for modeling chemistry, which had 325 i I specially thank Dr. Urmila Ghia, for supporting me all the time. I would like to thank Ohio Supercomputer Center for letting me use the resources.I would like to thank my friends and people from work, for being patient, cooperative and supportive all these years in Cincinnati. All this could not be possible without my parents and my older brother. I so grateful to my parents and my brother for always believing in me.Their unconditional love and support always made me to dream big and achieve my dreams with ease. Finally, I am so thankful to my Master and Sir for their continuous blessings and guidance throughout my life . v

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