Experiments on swirl stabilized non-premixed natural gas flames in a model gasturbine combustor

Janus, Bertram; Dreizler, Andreas; Janicka, J.

doi:10.1016/j.proci.2006.07.014

Cited by 41 publications

(18 citation statements)

References 26 publications

Supporting

Mentioning

Contrasting

Order By: Relevance

“…To investigate non-premixed combustion regimes with relevance to aircraft engines, Janus et al [12] experimentally characterized a model combustor (MOLECULES MOLECULES), consisting of a generic nozzle design with a single swirler assembly. The burner was operated at elevated pressure conditions and with preheated air.…”

Section: Introductionmentioning

confidence: 99%

Large eddy simulation of a partially-premixed gas turbine model combustor

See

Ihme

2015

Proceedings of the Combustion Institute

View full text Add to dashboard Cite

Section: Introductionmentioning

confidence: 99%

Large eddy simulation of a partially-premixed gas turbine model combustor

See

Ihme

2015

Proceedings of the Combustion Institute

View full text Add to dashboard Cite

“…Such gas turbine model combustors (GTMC) exhibit many of the features of the practical systems, such as self-excited thermo-acoustic instabilities and precessing vortex cores, while remaining sufficiently manageable that experimental measurements can provide significant physical insight and detailed model validation data [37][38][39][40][41][42][43][44][45][46][47][48][49]. In the present study, a laboratory scale gas turbine combustor has been investigated under thermo-acoustically unstable conditions at atmospheric pressure.…”

Section: Introductionmentioning

confidence: 99%

Flow–flame interactions causing acoustically coupled heat release fluctuations in a thermo-acoustically unstable gas turbine model combustor

Steinberg

Boxx

Stöhr

et al. 2010

Combustion and Flame

264

148

View full text Add to dashboard Cite

a b s t r a c tA detailed analysis of the flow-flame interactions associated with acoustically coupled heat-release rate fluctuations was performed for a 10 kW, CH 4 /air, swirl stabilized flame in a gas turbine model combustor exhibiting self-excited thermo-acoustic oscillations at 308 Hz. High-speed stereoscopic particle image velocimetry, OH planar laser induced fluorescence, and OH* chemiluminescence measurements were performed at a sustained repetition rate of 5 kHz, which was sufficient to resolve the relevant combustor dynamics. Using spatio-temporal proper orthogonal decomposition, it was found that the flow-field contained several simultaneous periodic motions: the reactant flux into the combustion chamber periodically oscillated at the thermo-acoustic frequency (308 Hz), a helical precessing vortex core (PVC) circumscribed the burner nozzle at 515 Hz, and the PVC underwent axial contraction and extension at the thermo-acoustic frequency. The global heat release rate fluctuated at the thermo-acoustic frequency, while the heat release centroid circumscribed the combustor at the difference between the thermoacoustic and PVC frequencies. Hence, the three-dimensional location of the heat release fluctuations depended on the interaction of the PVC with the flame surface. This motivated the compilation of doubly phase resolved statistics based on the phase of both the acoustic and PVC cycles, which showed highly repeatable periodic flow-flame configurations. These include flames stabilized between the inflow and inner recirculation zone, large-scale flame wrap-up by the PVC, radial deflection of the inflow by the PVC, and combustion in the outer recirculation zones. Large oscillations in the flame surface area were observed at the thermo-accoustic frequency that significantly affected the total heat-release oscillations. By filtering the instantaneous reaction layers at different scales, the importance of the various flow-flame interactions affecting the flame area was determined. The greatest contributor was large-scale elongation of the reaction layers associated with the fluctuating reactant flow rate, which accounted for approximately 50% of the fluctuations. The remaining 50% was distributed between fine scale stochastic corrugation and large-scale corrugation due to the PVC.

show abstract

“…In some research groups, high-pressure test rigs have been equipped with optical access in order to apply these techniques to GT combustion processes under realistic conditions, i.e. preheated air, high thermal loads, high turbulence levels and relevant combustor geometries, see for example [15][16][17][18][19][20][21][22][23][24].…”

Section: Introductionmentioning

confidence: 99%

PIV, 2D-LIF and 1D-Raman measurements of flow field, composition and temperature in premixed gas turbine flames

Stopper

Aigner

et al. 2010

Experimental Thermal and Fluid Science

View full text Add to dashboard Cite

a b s t r a c tSeveral laser diagnostic measurement techniques have been applied to study the lean premixed natural gas/air flames of an industrial swirl burner. This was made possible by equipping the burner with an optical combustion chamber that was installed in the high-pressure test rig facility at the DLR Institute of Combustion Technology in Stuttgart. The burner was operated with preheated air at various operating conditions with pressures up to p = 6 bar and a maximum thermal power of P = 1 MW.The instantaneous planar flow field inside the combustor was studied with particle image velocimetry (PIV). Planar laser induced fluorescence (PLIF) of OH radicals on a single-shot basis was used to determine the shape and the location of the flame front as well as the spatial distribution of reaction products. 1D laser Raman spectroscopy was successfully applied for the measurement of the temperature and the concentration of major species under realistic gas turbine conditions.Results of the flow field analysis show the shape and the size of the main flow regimes: the inflow region, the inner and the outer recirculation zone. The highly turbulent flow field of the inner shear layer is found to be dominated by small and medium sized vortices. High RMS fluctuations of the flow velocity in the exhaust gas indicate the existence of a rotating exhaust gas swirl. From the PLIF images it is seen that the primary reactions happened in the shear layers between inflow and the recirculation zones and that the appearance of the reaction zones changed with flame parameters. The results of the multiscalar Raman measurements show a strong variation of the local mixture fraction allowing conclusions to be drawn about the premix quality. Furthermore, mixing effects of unburnt fuel and air with fully reacted combustion products are studied giving insights into the processes of the turbulence-chemistry interaction.

show abstract

Experiments on swirl stabilized non-premixed natural gas flames in a model gasturbine combustor

Cited by 41 publications

References 26 publications

Large eddy simulation of a partially-premixed gas turbine model combustor

Large eddy simulation of a partially-premixed gas turbine model combustor

Flow–flame interactions causing acoustically coupled heat release fluctuations in a thermo-acoustically unstable gas turbine model combustor

PIV, 2D-LIF and 1D-Raman measurements of flow field, composition and temperature in premixed gas turbine flames

Contact Info

Product

Resources

About