Investigations of swirl flames in a gas turbine model combustor

Meier, Wolfgang; Duan, Xuru; Weigand, Peter

doi:10.1016/j.combustflame.2005.07.009

Cited by 138 publications

(172 citation statements)

References 29 publications

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“…Local extinction in the flame root region has also been found in two previous studies of the same combustor. Using Raman spectroscopy, Meier et al found a large number of partially reacted mixtures in this region and concluded that these are an indication for local extinction [18]. A time-resolved visualization of local extinction in the flame root region using high-speed laser diagnostics has been reported by Boxx et al [15].…”

Section: Flame Rootmentioning

confidence: 99%

“…The swirl number S has been estimated from LDV measurements as S≈0.55, and the Reynolds number of the cold air as Re≈15000 [17,18]. At this condition, phases of stable operation are intermittently interrupted by transient events of blowout and reignition, which appear randomly in time without any previous changes of the mean flame shape.…”

Section: Combustor and Flamementioning

confidence: 99%

“…The temperatures in the IRZ are significantly higher than those in the ORZ, which results from the relatively rich and lean conditions, respectively. For a more detailed discussion of the thermochemical state of the flame, we refer to [17,18]. Figure 4 shows an instantaneous OH* chemiluminescence image during stable operation.…”

Section: Measuring Techniquesmentioning

confidence: 99%

“…Distributions of average mixture fraction and temperature, which were measured in a previous study using Raman spectroscopy [17,18], are shown in ume originating from the fuel nozzle. For methane and air, the stoichiometric value is f stoich =0.055, and the value for φ global =0.55 is f global =0.031.…”

Section: Measuring Techniquesmentioning

confidence: 99%

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Dynamics of lean blowout of a swirl-stabilized flame in a gas turbine model combustor

Stöhr

Boxx

Carter

et al. 2011

Proceedings of the Combustion Institute

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119

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Lean blowout (LBO) of a partially premixed swirl flame is studied using chemiluminescence imaging and simultaneous stereo-PIV and OH-PLIF measurements at repetition rates up to 5 kHz. The flame, which is operated with methane and air in a gas turbine model combustor at atmospheric pressure, features a pronounced precessing vortex core (PVC) at the inner shear layer. In the first part of the study, the stabilization mechanism of the flame close to LBO is investigated. The fields of velocity and OH show that near LBO there are essentially two regions where reaction takes place, namely the helical zone along the PVC and the flame root around the lower stagnation point. The zone along the PVC is favorable to the flame due to low strain rates in the vortex center and accelerated mixing of burned and fresh gas. The flame root, which is located close to the nozzle exit, is characterized by an opposed flow of hot burned gas and relatively fuel-rich fresh gas. Due to the presence of high strain rates, the flame root is inherently unstable near LBO, featuring frequent extinction and re-ignition. The blowout process, discussed in the second part of the study, starts when the extinction of the flame root persists over a critical length of time. Subsequently, the reaction in the helical zone can no longer be sustained and the flame finally blows out. The results highlight the crucial role of the flame root, and suggest that well-aimed modifications of flow field or mixture fraction in this region might shift the LBO limit to leaner conditions.

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Section: Flame Rootmentioning

confidence: 99%

Section: Combustor and Flamementioning

confidence: 99%

Section: Measuring Techniquesmentioning

confidence: 99%

Section: Measuring Techniquesmentioning

confidence: 99%

See 2 more Smart Citations

Dynamics of lean blowout of a swirl-stabilized flame in a gas turbine model combustor

Stöhr

Boxx

Carter

et al. 2011

Proceedings of the Combustion Institute

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221

119

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“…The gas turbine model combustor, extensively studied experimentally e.g. in [9,8], is schematically shown in Figure 2 (left). Dry air at room temperature and atmospheric pressure is supplied to the combustion chamber through two concentric co-swirling nozzles.…”

Section: Test-case Geometry Scales and Numerical Methodsmentioning

confidence: 99%

A five dimensional implementation of the flamelet generated manifolds technique for gas turbine application

Donini¹,

Bastiaans²,

Oijen³

et al. 2015

AIP Conference Proceedings

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, de, L. P. H. (2015). A five dimensional implementation of the flamelet generated manifolds technique for gas turbine application. AIP Conference Proceedings, 1648, 030012-1/5. DOI: 10.1063/1.4912329 General rightsCopyright and moral rights for the publications made accessible in the public portal are retained by the authors and/or other copyright owners and it is a condition of accessing publications that users recognise and abide by the legal requirements associated with these rights.• Users may download and print one copy of any publication from the public portal for the purpose of private study or research.• You may not further distribute the material or use it for any profit-making activity or commercial gain • You may freely distribute the URL identifying the publication in the public portal ? Take down policyIf you believe that this document breaches copyright please contact us providing details, and we will remove access to the work immediately and investigate your claim. Abstract. In the present paper the Flamelet-Generated Manifold (FGM) chemistry reduction method is implemented and extended for the inclusion of all the features that are typically observed in stationary gas-turbine combustion. These consist of stratification effects, heat loss and turbulence. The latter is included by coupling FGM with the Reynolds Averaged Navier Stokes (RANS) model. Three control variables are included for the chemistry representation: the reaction evolution is described by the reaction progress variable, the heat loss is described by the enthalpy and the stratification effect is expressed by the mixture fraction. The interaction between chemistry and turbulence is considered through a presumed probability density function (PDF) approach, which is considered for progress variable and mixture fraction. This results in two extra control variables: progress variable variance and mixture fraction variance. The resulting manifold is five-dimensional, in which the dimensions are progress variable, enthalpy, mixture fraction, progress variable variance and mixture fraction variance. In addition, a highly turbulent and swirling flame in a gas turbine model combustor is computed, in order to test the 5-D FGM implementation. The use of FGM as a combustion model shows that combustion features at gas turbine conditions can be satisfactorily reproduced with a reasonable computational effort. The implemented combustion model retains most of the physical accuracy of a detailed simulation while drastically reducing its computational time, paving the way for new developments of alternative fuel usage in a cleaner and more efficient combustion.

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Spontaneous Raman Scattering Diagnostics: Applications in Practical Combustion Systems

Kojima

Nguyen

2010

Handbook of Combustion

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In this chapter, the practical aspects of spontaneous Raman scattering (SRS) diagnostics are explained based on hands‐on experience in applications to high‐pressure combustion. Details of the state‐of‐the‐art instrumentation used in an advanced vibrational Raman spectroscopy apparatus for combustion diagnostics are described, after which techniques are discussed for the design and optimization of a temporally stretched pulsed‐laser Raman excitation system used in conjunction with a relatively low‐spectral resolution, high‐optical throughput Raman spectrograph system. This system enables a true single‐shot diagnostic capability for turbulent flame studies. Single‐shot‐capable Raman diagnostic systems demand both a high signal‐to‐noise ratio and a high dynamic range in order to accurately capture Raman scattering occurring in the turbulent combustion process. A brief account of the data reduction and post‐processing methodology used to obtain multiscalar information (temperature and species concentrations) via the calibration matrix formalism is then provided. Finally, the concepts and methodology are applied to a high‐pressure swirl‐stabilized flame are outlined, demonstrating the capabilities of an SRS system in a practical combustion device. Practical considerations on the use of calibration burners and flow control systems for high‐pressure combustion systems are also addressed.

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Investigations of swirl flames in a gas turbine model combustor

Cited by 138 publications

References 29 publications

Dynamics of lean blowout of a swirl-stabilized flame in a gas turbine model combustor

Dynamics of lean blowout of a swirl-stabilized flame in a gas turbine model combustor

A five dimensional implementation of the flamelet generated manifolds technique for gas turbine application

Spontaneous Raman Scattering Diagnostics: Applications in Practical Combustion Systems

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