Combustion characteristics of a model can-type combustor

Bicen, A. F.; Tse, D. G. N.; Whitelaw, J. H.

doi:10.1016/0010-2180(90)90120-g

Cited by 31 publications

(23 citation statements)

References 12 publications

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“…The combustor is located in a large duct and is effectively "plenum fed" so that the primary and dilution jets enter the combustor at approximately 90 • to its axis. The combustor geometry is described in greater detail in [23,29]. A schematic representation of the combustor is shown in Fig.…”

Section: Flow Configurationmentioning

confidence: 99%

“…The configuration selected in the present work is a model can-type combustor closely representative of that found in the Rolls-Royce Tay engine. The combustor, described in [23][24][25], comprises rows of primary and dilution ports, a circular to rectangular nozzle, as well as of porous walls, and the resulting flow pattern is extremely complex and is well suited to an investigation of the capabilities of LES. In the present work, the conserved scalar approach has been adopted to model the combustion process, both in view of the advantages offered by the method over more expensive, although more rigorous alternatives, and because of its success in previous works [16,17,26].…”

Section: Introductionmentioning

confidence: 99%

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Large eddy simulation of a model gas turbine combustor

Mare

Jones

Menzies

2004

Combustion and Flame

161

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Section: Flow Configurationmentioning

confidence: 99%

Section: Introductionmentioning

confidence: 99%

Large eddy simulation of a model gas turbine combustor

Mare

Jones

Menzies

2004

Combustion and Flame

161

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“…the black body intensity (Ī b ), depend on the flame temperature; and the absorption coefficient, κ, which is considered to be a function of the mole fractions of H 2 O and CO 2 . A good agreement was achieved when di Mare et al [15] compared these computational results ofT ,Ỹ H2O andỸ CO2 against experimental measurements of Bicen et al [9], which will not be repeated here. In this figure we can also see that the total radiative intensity attains a maximum at the region where both the temperature and absorption coefficient are maximum.…”

Section: Resultsmentioning

confidence: 65%

“…1, which is representative of the Rolls-Royce Tay gas turbine [9]. The combustor walls are made of transply, a laminated porous material.…”

Section: Introductionmentioning

confidence: 99%

Radiative heat transfer in a model gas turbine combustor

Paul¹,

Jones²

2006

WIT Transactions on Engineering Sciences, Vol 53

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In this paper we have carried out a three-dimensional numerical study to investigate the radiative heat transfer in a model gas turbine combustor, representative of the Rolls-Royce Tay combustor. The Discrete Ordinate Method (DOM/Sn) in general body-fitted co-ordinate system is applied to solve the filtered Radiative Transfer Equation (RTE) for the radiation modelling and this has been combined with a Large Eddy Simulation (LES) of the flow, temperature and composition fields within the combustion chamber. The radiation considered in this work is due only to the hot combustion gases notably carbon dioxide (CO 2 ) and water vapour (H 2 O) also known as non-luminous radiation. The instantaneous results of the radiation properties such as the incident radiation and the radiative energy source or sink as the divergence of the radiative heat fluxes are computed inside the combustion chamber and presented graphically.

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“…Reacting flow studies of jets in a crossflow have been conducted in both conventional and RQL combustor configurations to complement the non-reacting studies and assess the impact of heat release on the mixing processes [24][25][26][27][28][29].…”

Section: Reacting Jic Mixingmentioning

confidence: 99%

Experimental and modeling investigation of the effect of air preheat on the formation of NOx in an RQL combustor

et al. 2012

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The Rich-burn/Quick-mix/Lean-burn (RQL) combustor concept has been proposed to minimize the formation of oxides of nitrogen (NO x ) in gas turbine systems. The success of this low-NO x combustor strategy is dependent upon the links between the formation of NO x , inlet air preheat temperature, and the mixing of the jet air and fuel-rich streams. Chemical equilibrium and kinetics modeling calculations and experiments were performed to further understand NO x emissions in an RQL combustor. The results indicate that as the temperature at the inlet to the mixing zone increases (due to preheating and/or operating conditions) the fuel-rich zone equivalence ratio must be increased to achieve minimum NO x formation in the primary zone of the combustor. The chemical kinetics model illustrates that there is sufficient residence time to produce NO x at concentrations that agree well with the NO x measurements. Air preheat was found to have very little effect on mixing, but preheating the air did increase NO x emissions significantly. By understanding the mechanisms governing NO x formation and the temperature dependence of key reactions in the RQL combustor, a strategy can be devised to further reduce NO x emissions using the RQL concept. List of symbolsNumber of round holes in quick-mix module R Radius of the quick-mix module r Radial distance from the module center S Orifice spacing U Axial velocity U M Unmixed mainstream velocity V J Jet exit velocity x Downstream distance; x = 0 at orifice leading edge q J Density of jet flow q M Density of mainstream flow / Equivalence ratio = (fuel/air) actual /(fuel/air) stoichiometric

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Combustion characteristics of a model can-type combustor

Cited by 31 publications

References 12 publications

Large eddy simulation of a model gas turbine combustor

Large eddy simulation of a model gas turbine combustor

Radiative heat transfer in a model gas turbine combustor

Experimental and modeling investigation of the effect of air preheat on the formation of NOx in an RQL combustor

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