High-speed laser diagnostics for the study of flame dynamics in a lean premixed gas turbine model combustor
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- Boxx, I., Arndt, C.M., Carter, C.D. et al. Exp Fluids (2012) 52: 555. doi:10.1007/s00348-010-1022-x
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A series of measurements was taken on two technically premixed, swirl-stabilized methane-air flames (at overall equivalence ratios of ϕ = 0.73 and 0.83) in an optically accessible gas turbine model combustor. The primary diagnostics used were combined planar laser-induced fluorescence of the OH radical and stereoscopic particle image velocimetry (PIV) with simultaneous repetition rates of 10 kHz and a measurement duration of 0.8 s. Also measured were acoustic pulsations and OH chemiluminescence. Analysis revealed strong local periodicity in the thermoacoustically self-excited (or ‘noisy’) flame (ϕ = 0.73) in the regions of the flow corresponding to the inner shear layer and the jet-inflow. This periodicity appears to be the result of a helical precessing vortex core (PVC) present in that region of the combustor. The PVC has a precession frequency double (at 570 Hz) that of the thermo-acoustic pulsation (at 288 Hz). A comparison of the various data sets and analysis techniques applied to each flame suggests a strong coupling between the PVC and the thermo-acoustic pulsation in the noisy flame. Measurements of the stable (‘quiet’) flame (ϕ = 0.83) revealed a global fluctuation in both velocity and heat-release around 364 Hz, but no clear evidence of a PVC.
Gas turbine (GT) relevant flames stabilized by swirl exhibit large effects of flow and flame dynamics like vortex breakdown, precessing helical structures, local flame extinction, and/or thermo-acoustic combustion instabilities. Efforts to understand the turbulence-chemistry interactions of combustion in lean premixed and partially premixed swirl flames in gas turbine combustors have led in recent years to the application of multiple, complementary measuring techniques, in particular 2D laser measuring techniques. The simultaneous application of particle image velocimetry (PIV) and planar laser-induced fluorescence (PLIF) has, for example, contributed to a better understanding of the flow-field/flame interaction in swirl flames (Petersson et al. 2007; Tanahashi et al. 2005; Sadanandan et al. 2008; Stöhr et al. 2009). These techniques provide minimally intrusive measurements in otherwise inaccessible environments such as in high-pressure test rigs and combustion chambers. Research groups have performed laser-based measurements in high-pressure test rigs with optical access in order to investigate GT combustion processes under realistic conditions, i.e. with preheated air, high thermal loads, high turbulence levels, and relevant combustor geometries (Lee et al. 2000; Meier et al. 2000; Löfström et al. 2000; Gord et al. 2002; Kojima and Nguyen 2004; Willert et al. 2006; Griebel et al. 2007; Janus et al. 2007; Stopper et al. 2008; Strakey et al. 2008; Ax et al. 2009). While these investigations have contributed significantly to a better understanding of certain aspects of GT combustion under pressure, such complex and expensive experiments do not (and, indeed, cannot) result in systematic or comprehensive characterization of swirl flames and are often affected by uncertainties in the boundary conditions, originating, e.g., from limited optical access or a contribution from cooling air to the combustion. High-pressure technical scale (in the MW-range) combustion rigs also degrade the peak performance of most 2D laser measurement techniques through beam-steerage, laser absorption and backscatter, pressure broadening of molecular transitions, fluorescence trapping, and decreased OH concentrations resulting from increased three-body recombination rates. Alternatively, the use of model combustors that can be operated under atmospheric-pressure laboratory conditions has proven to be a good concept to (1) gain insight into the interplay between the turbulent swirling flow-field and the flame chemistry and (2) acquire reliable experimental data suitable for model validation.
The relatively low repetition rate (typically ≈ 10 Hz) of previously applied planar laser measuring systems such as PLIF of OH radicals and PIV has lead to extensive reliance on series of non-correlated single-shot images or time-averaged measurements in turbulent flames. In flames with periodic combustion phenomena such as thermo-acoustic oscillation, phase-correlated single-shot and averaged measurements have been taken. Extensive databases of high-resolution measurements suitable for numerical and code-validation studies have been so acquired. Thorough analysis, in particular using spectral and proper orthogonal decomposition (POD) methods, has reinforced insight gained by these techniques, but unfortunately, phase-averaged measurements can only isolate mean and statistical cyclic variations of thermo-dynamic and thermo-chemical properties. Information on temporally developing, transient and non-periodic phenomena is lost. Reynolds Averaged Navier–Stokes (RANS) simulations are similarly limited. A fully resolved (temporally and spatially) direct numerical simulation with detailed chemistry and sufficient run duration to be statistically relevant is well beyond the state of the art; furthermore, large eddy simulation (LES) techniques rely on sub-grid scale models that, in many cases, have not been validated under technically relevant operating conditions.
A logical extension of phase-resolved measurement techniques and quasi-steady numerical simulations using techniques such as RANS is the acquisition of long-duration, time-resolved planar measurements of similar flow-field quantities. Although multi-shot planar-LIF imaging with short inter-frame separation has been used extensively by previous researchers (Kychakoff et al. 1987; Seitzman et al. 1994; Schefer et al. 1994; Kaminski et al. 1999; Watson et al. 2002; Hult et al. 2005; Tanahashi et al. 2005; Tanahashi et al. 2008), such measurements are of limited use in extracting time series and frequency characteristics in complex flames. As demonstrated by (Upatnieks et al. 2004; Steinberg et al. 2008; Boxx et al. 2009a, b, c, d), long-duration, high-speed planar measurements allow one to track specific flow-field-flame interactions as they occur, simplifying the interpretation of such data. The acquisition of a statistically significant number of sequential cycles (e.g., several 100) in a single run also renders such interpretations more reliable. Being able to acquire measurements at kHz rates also results in a short (absolute) acquisition time, a significant advantage in cases where window fouling can be problematic. The present work describes a unique and extremely capable new planar diagnostic system capable of simultaneously acquiring the three-component velocity field and the relative OH distribution at repetition rates of 10 kHz over measurement durations of 0.8 s. The system was applied to the study of a 25 and a 30 kW, technically premixed, swirl-stabilized methane-air flame in a gas turbine model combustor. One flame burned stably, and the other exhibited strong self-excited thermo-acoustic pulsation.
2 High frame rate planar measurement system
The kHz measuring system consists of two independent laser-based measuring systems: a stereoscopic PIV system and a PLIF system configured for OH detection. Both systems are designed for operation at 10 kHz over 0.8 s durations and have spatial resolution and signal to noise ratios comparable to that of conventional 10 Hz systems.
2.1 10 kHz PLIF system
The 10 kHz PLIF system uses a frequency-doubled dye laser (Sirah Credo), pumped with a frequency-doubled, diode-pumped solid state Nd:YAG laser (Edgewave IS-8IIE), which operated at 532 nm wavelength. At 10 kHz, the pump laser delivered 4 mJ/pulse (40 W average output) with 8.5 ns pulse duration. The active medium of the dye laser was Rhodamine 6G in Ethanol (0.09 g/L concentration). This dye laser uses a low-threshold resonator cavity optimized for the relatively low pulse energies associated with kHz-rate pump lasers. As a result, this laser is considerably more efficient than the 5-kHz laser used in an earlier configuration of this system (described in Boxx et al. 2009a, b, c, d). A β-barium borate (BBO) crystal, housed in a temperature controlled oven, was used for frequency doubling of the dye laser beam. Isolation of the fundamental and frequency-doubled beams was accomplished with a four-prism beam separator. At 10-kHz pump frequency, the time-average output from the dye laser at 283.2 nm was ≈1.4 W or 0.14 mJ/pulse. Although higher pulse energies are possible, this comes with an increased risk of damaging either the BBO crystal or the four-prism wavelength separation unit. As such, the laser was operated at ≈1.4 W during the experiments described here.
The wavelength tuning of the dye laser to the peak of the isolated Q1(7) line of the A–X (1–0) transition of OH was checked daily using a setup consisting of a laminar reference flame, a 10-cm monochromator (Jobin–Yvon H10-UV), and a photomultiplier tube for fluorescence detection. The laser line width at 566 nm was 0.06 cm−1, and thus, the value at 283 nm is expected to be <0.1 cm−1.
The resulting fluorescence emission was acquired with a high frame-rate CMOS camera (LaVision HSS5) and an external, two-stage, lens-coupled intensifier (LaVision HS-IRO). The intensifier uses a 25-mm diameter S20 photocathode with a P47 phosphor in its first stage and a S20T/P46 for the second (booster) stage. The HSS5 camera has an array size of 1,024 × 1,024 pixels (each 17-μm square) and is digitized to 10-bits. The camera operates in full-frame mode at 3,000 frames per second (fps) and possesses 2.6 GB of onboard memory. This corresponds to approximately 0.8 s of acquisition time at a 10-kHz frame rate.
Fluorescence from the A–X (1–1) and (0–0) bands was collected at 310 nm with a fast Cerco 45 mm, f/1.8 objective lens. Background luminosity was reduced using a short (200–500 ns, depending on run conditions) intensifier gate. Elastic scattering at 283 nm was blocked using a high-transmission (>80% at 310 nm) bandpass interference filter (Laser-Components GmbH). Flat-field correction for spatial variation of the laser sheet-intensity and other imaging non-uniformities was accomplished using a mean image derived from laser-induced fluorescence of acetone vapor that was doped into the combustion chamber (to be described later). The same intensifier and collection optics were used (separately) with a HSS6 CMOS camera (described below) to also image chemiluminescence emission of the electronically excited OH (OH*). Emission from OH* is a good qualitative marker of global heat-release (Docquier and Candel 2002; Lee and Santavicca 2003; Hardalupas and Orain 2004).
2.2 10-kHz PIV system
The PIV system is based on a dual-cavity, diode-pumped, solid state Nd:YAG laser (Edgewave, IS-6IIDE) and a pair of CMOS cameras (LaVision HSS6). The laser produces 2.6 mJ/pulse at 532 nm at repetition rates up to 10 kHz. Pulse duration is ≈14 ns. Pulse timing separation for the PIV system in this study was set to between Δt = 5 and 10 μs (depending on run conditions), with the OH-PLIF excitation pulses temporally interlaced between the first and second PIV pulse of the measurement cycle. As with the PLIF system, three cylindrical lenses were used to form the sheet: fpiv1 = −25 mm, fpiv2 = 300 mm, and fpiv3 = 1,000 mm. To minimize noise arising from inter-frame particle dropout, the beam waist was located somewhat beyond the probe region. The sheet thicknesses were measured in the same manner as for the PLIF beam; at the probe volume, the sheet thickness was ≤0.7 mm. Mie scattering from titanium dioxide (TiO2) particles seeded into the flow was imaged using CMOS cameras mounted on opposite sides of the laser sheet in a forward-scatter imaging configuration. The cameras have a 12-bit, 1,024 × 1,024 pixel imaging arrays (20 μm square pixels) and are capable of imaging at up to 5,400 fps in full-frame mode. Operated in two-frame PIV mode at 10 kHz (so that the camera frames at 20 kHz), this array size is reduced to 512 × 512 pixels. The PIV cameras had sufficient onboard memory (8 GB) to match the acquisition time of the OH-PLIF camera in a given experiment run. Scattered light was collected with 100-mm macro-lenses (Tokina), and image-blur due to off-axis defocusing was corrected using Scheimpflug adaptors between the lenses and cameras. The relatively short integration time (50 μs) eliminated the need for interference or colored-glass filters in front of the lens. Perspective distortion was corrected using a dual-plane, 3D imaging target (LaVision Type 7). The same target was used to map the fields of view of the PIV and PLIF systems to one another. Image mapping, calibration, and particle cross-correlations were completed using a commercial, multi-pass adaptive window offset cross-correlation algorithm (LaVision DaVis 7.2). Final PIV window size and overlap were 16 × 16 pixels and 50%, respectively. The field of view for the PIV measurements was ≈36 × 36 mm.
3 Burner and run conditions
The present work focuses on the Turbomeca Gas Turbine Model Combustor (TM-Burner), shown in Fig. 1b. The TM-Burner is a laboratory-scale swirl burner based on an industrial design by Turbomeca S.A. and is operated with a lean CH4-air flame at atmospheric pressure. Dry air at room temperature is fed via a 78-mm diameter plenum into a central nozzle through 12 radial swirl-vanes. Fuel is injected directly into the swirler through twelve 1-mm diameter holes. The injection of the fuel at high momentum into the air flow at the swirler results in relatively good fuel–air mixing upstream of the optical combustion chamber, and thus, this design is referred to as technically premixed. The exit of the burner nozzle has a diameter of 27.85 mm and has a rounded, conical centerbody. The nozzle is mounted in a combustion chamber with a square, 85 × 85 mm cross-section. The chamber stands 114 mm tall and is enclosed by 1.5-mm thick fused silica window plates, which are supported by posts at each corner. Gas exits the combustion chamber through a thick metal plate with a conical contraction to a 40-mm diameter exhaust tube. The excellent optical access, compact size, and moderate thermal load (≈30 kW) of this burner make both point- and planar-laser measurement techniques feasible (albeit challenging) under laboratory conditions.
Two CH4-air flames were studied in this experiment: a 25 kW flame with strong self-excited thermo-acoustic pulsations (the ‘noisy flame’) and a 30 kW flame that burns stably and without strong thermo-acoustic pulsation (the ‘quiet flame’). These run conditions were chosen to replicate those studied by Meier et al. (2007), designated Flame 1 and Flame 2a, respectively. The Reynolds number of the flame is approximately 35,000, based on cold-flow conditions at the nozzle exit. Meier et al. (2007) estimate the Kolmogorov scale of the flame to be on the order of 0.1 mm, with a corresponding timescale of 35 μs. This is clearly much smaller than the spatio-temporal resolution of the measuring system, and no attempt is made in this work to analyze the turbulence-chemistry interaction at this scale. The dominant thermo-acoustic pulsation, however, (measured at approximately 290 Hz by Meier et al. 2007), is well within the temporal resolution of the measurement system.
For each run condition, fuel and air were metered into the burner via electromechanical mass flow controllers. Air was supplied at a rate of 740 g/min, which was slightly higher than the 734 g/min value stated by Meier et al. (2007) but within the accuracy of the flow rate measurement. Approximately 4% of the air flow was delivered to the burner through a fluidized bed particle seeder. The noisy and quiet flames had equivalence ratios of 0.73 and 0.83, corresponding to 30 and 36 g/min CH4 for the noisy and quiet flame conditions, respectively. Flow rates of the fuel, seed-air, and main-flow air were monitored throughout the experiment via calibration-standard Coriolis mass flowmeters (Siemens Sitrans-FC MassFlo 2,100, Model DI-1.5, DI-3 and DI-15, respectively).
Pressure fluctuations in the burner were measured with two microphones (Brüel & Kjaer, Type 4,939): one mounted in a corner post of the combustion chamber and one in the plenum. The microphones were sampled simultaneously with the gate monitor signals of the image intensifiers in order to directly identify the phase of the thermo-acoustic cycle for each PLIF and PIV image.
The burner was operated at the run condition for at least 20 min prior to each experimental run to allow it to thermally stabilize. During this warm-up period, no seed particles were delivered to the air flow. Shortly, before a measurement, the bulk air flow was reduced by approximately 4%, and the same amount was metered into the flow via the particle seeder using a separate electromechanical flow controller. This ensured reliable, reproducible seed density for each run, while minimizing seed-buildup on the combustor windows during the warm-up period.
4 Results and discussion
4.1 Mean flame characteristics
4.2 Time-dependent phenomena
The power spectrum of axial velocity for the quiet flame shows a strong peak at 360–370 Hz for all three monitor points and for the integrated OH* signal. This indicates that although the flame is quiet, it still has a periodic fluctuation at a characteristic frequency. Given the weakness of the acoustic signal relative to that measured in the noisy flame, this frequency likely represents a damped resonance mode of the combustor for this flame condition. As the spectra uniformly peak at the same frequency at all three spatial locations, the pulsation is not likely indicative of a characteristic fluid-dynamic structure such as a vortex shedding induced by the swirl.
The corresponding power spectra for the noisy flame show starkly different behavior. All four plotted spectra show strong peaks at approximately 280–290 Hz, which corresponds to the dominant thermo-acoustic oscillation. This peak was also observed in the simultaneously measured acoustic signal. The spectra of integrated OH* emission and axial velocity in the IRZ show a single peak at this frequency and minor secondary peaks at 560–570 Hz. The spectra for the ISL and Jet-regions also show peaks at 560–570 Hz, albeit with the same order of magnitude as those at the thermo-acoustic frequency. These spectra indicate a very strong periodic flow-field phenomenon occurring locally within the ISL and Jet-inflow region. The nature of this flow structure is not immediately clear, given the wide range of fluid-dynamic instabilities known to affect shear layers in a swirl-stabilized combustor. The lack of a corresponding peak in the spectra of the integrated OH* signal indicates that the phenomenon occurring at 570 Hz in the ISL and Jet-region does not significantly affect the global heat-release of the flame, which varies at the dominant thermo-acoustic pulsation frequency (i.e., 280–290 Hz). The fact that the second peak occurs at twice the thermo-acoustic frequency, however, suggests the periodic flow structure is, in fact, linked somehow to the thermo-acoustic pulsation.
4.3 POD analysis
In order to identify the fluid-dynamic phenomena responsible for the peaks seen at 570 Hz in the power spectra of axial velocity, a proper orthogonal decomposition (POD) was performed on the PIV data. POD is a well-established technique in the field of fluid mechanics (Berkooz et al. 1993). The result of the POD is a set of orthogonal eigenmodes, representing coherent flow structures ordered by their contribution to the turbulent kinetic energy. For each eigenmode, temporal mode coefficients can be obtained by taking the scalar products of the instantaneous flow-fields with the eigenmode. In the present case, the POD was calculated using the method of snapshots (Sirovich 1987) based on a series of 4,096 sequential PIV measurements, acquired at 10 kHz.
Taken together, the eigenmodes indicate the presence of a helical precessing vortex core (PVC) in the flow-field of the noisy flame. In addition, the eigenmodes indicate that the PVC is the dominant coherent flow structure in this case and that it has a precession frequency of 570 Hz. This finding is reinforced by the numerical simulations of Roux et al. (2005), who predicted the existence of a helical PVC with a precession frequency of 540 Hz in the same combustor for similar flow rates, albeit under non-reacting flow conditions. In contradistinction to the simulation of Roux et al. (2005), it does not appear that combustion damps out the PVC in this case. Rather, the PVC remains both present and has a strong influence on both the flame and turbulent flow-field under these conditions. The relatively minor fluctuation observed in the integrated emission from OH* at 570 Hz, however, indicates that the PVC does not significantly affect the global heat-release of the flame; nonetheless, it may reasonably be expected to have a major influence on local turbulence-chemistry interaction and flame dynamics. This possibility is reinforced by Fig. 3c, discussed earlier, wherein the mean reaction-zone location is shown to be different for the noisy flame compared to that of the quiet flame.
In this image sequence, we see the in-plane component of the PVC structure, together with the coupling mechanism by which it interacts with the thermo-acoustic pulsation. In the first frame, we see two vortices, the first having positive (out-of-plane) vorticity, centered at (x, y) = (+15, +27 mm) and the second, having negative (into-plane) vorticity centered at (−10, 13 mm). One also sees an opposed-flow stagnation point at (5, 11 mm), where the inflow with strong positive axial velocity meets negative axial velocity fluid from the IRZ. The reaction zones identified in this measurement are highly fragmented and discontinuous but tend to conform to the passage of these characteristic large-scale flow structures. The reaction zone in frame 1 appears to lie primarily along the periphery of the large-scale vortices identified in the flow, with wrinkles visible near the interaction of the vortices with the stagnation-point flow within the IRZ. At the location of the stagnation point, the reaction zone is somewhat more contiguous than in other regions and tends to align, as one might expect, along the stagnation line between the inflow gases and the IRZ. The conformation of the reaction zone to the passage of large-scale propagating vortices is consistent with similar measurements in a dual-swirl combustor described in Boxx et al. (2009d).
In the measurements following frame 1, we see the two large-scale vortices propagate upward and radially outward from the centerline. The stagnation point is also seen to move downstream and to the right of centerline. In frame 3, we see the appearance of a new vortex to the right of centerline and another stagnation-point flow appear to the left, at (x, y) = (−3, 7 mm). Both of these then propagate downstream and radially outward from the centerline as before. At the same time, the fragmented and discontinuous reaction zone is seen to move downstream over the first half of the sequence. By frame 6, significant amounts of reaction zone are visible in the IRZ upstream, nearer to the nozzle. Given the sudden (in-plane) appearance and discontinuity of these reaction-zone fragments, it is not immediately clear what physical mechanism is responsible for this upstream appearance of the flame. Given the technically premixed fuel–air inflow, upstream flame propagation and bulk convection induced by the thermo-acoustic pulsation is clearly responsible for some portion of the observed upstream motion of the reaction zones. This motion may appear discontinuous in these planar measurements due to the high through-plane component of velocity. Similar behavior has been observed in previous studies (Boxx et al. 2009d). Given the extensive mixing of post-combustion fluid and technically premixed fuel–air inflow in the IRZ, auto-ignition appears to also be a viable explanation of the observed upstream appearance of reaction zones. Analysis of these two possibilities is ongoing, but a rigorous statistical analysis of each is beyond the scope of this paper.
With the appearance of significant amounts of reaction zone in the upstream region of the IRZ around frame 6, a much longer and more contiguous reaction zone forms in the near nozzle region. This section of reaction zone then begins once more to conform to the passage of large-scale vortices and align with the stagnation-point flow in a manner similar to that observed in frame 1. The velocity field by this point also bears a strong resemblance to that seen in frame 1, with two diagonally offset, counter-rotating large-scale vortices separated by a stagnation-point opposed flow.
Comparing this measurement sequence with the POD results, axial velocity spectra, and mean reaction-zone analysis raises a number of interesting questions regarding the coupling between the PVC and the thermo-acoustic pulsation. From the POD analysis, it appears that the dominant flow structures are a helical PVC and a thermo-acoustic pulsation. The POD temporal modes and axial velocity spectra indicate that this PVC has a characteristic frequency of approximately 570 Hz. The thermo-acoustic pulsation is known to be the dominant variable affecting global heat-release and occurs at ≈288 Hz, or approximately one half the PVC precession frequency. Inspection of the measurement sequence in Fig. 8 suggests the existence of a periodic axial fluctuation in reaction-zone location at approximately the thermo-acoustic frequency, evidenced by the similarity in reaction-zone structure in the first and last frame of the 0.33 ms duration sequence. A time series of OH* emission integrated over the same region confirms a 288-Hz fluctuation in heat-release near the nozzle. Over the same period, two large-scale vortical structures (those associated with the PVC) propagate through the field of view along the right-hand side of the central axis. The first vortex is seen to draw the reaction zone upward and radially outward from the nozzle, allowing the second to enter the combustion chamber absent a contiguous flame-sheet.
Although a rigorous statistical analysis of the PVC, reaction-zone structure, and thermo-acoustic oscillation is beyond the scope of the current work, it is clear that the three phenomena are closely coupled in the noisy flame. Previous work (Boxx et al. 2009d; Steinberg et al. 2010) has shown extensive coupling between PVC, reaction-zone dynamics, and thermo-acoustic pulsation in swirl-stabilized burners. The fact that the characteristic frequency of the PVC is an integer multiple of the thermo-acoustic oscillation suggests a particularly strong coupling in this burner, possibly strengthening the pulsation intensity. What remains to be seen in future analysis, however, is the physical mechanism responsible for this coupling, and whether the 570-Hz frequency of the PVC is a cause or an effect of the 288-Hz thermo-acoustic oscillation. Also yet to be determined is whether the coherent vortex identified in the noisy flame is a single-, or double-helical PVC.
A series of measurements was taken on two technically premixed, swirl-stabilized CH4-air flames in an optically accessible gas turbine model combustor. The burner (designed by Turbomeca S.A.) was operated with lean mixtures at atmospheric pressure. The two flames described here differed only in fuel flow rate and thus overall equivalence ratio: in one case the equivalence ratio was 0.83, and the flame was relatively quiet (the ‘quiet flame’); in the second case, the equivalence ratio was 0.73, and the flame exhibited a strong acoustic signature (the ‘noisy flame’). The primary diagnostics used were simultaneous planar laser-induced fluorescence (PLIF) of the OH radical and stereoscopic particle image velocimetry (PIV) acquired at repetition rates of 10 kHz over a measurement duration of 0.8 s. Also measured were acoustic pulsations and OH chemiluminescence. Proper orthogonal decomposition (POD) of the PIV time series measurements was the primary analysis tool and allowed calculation of the dominant energetic modes within each flame.
Analysis revealed a very dynamic and fragmented flame (from the OH-PLIF) and strong local periodicity in the thermoacoustically self-excited noisy flame (at about 288 Hz) in the regions of the flow corresponding to the inner shear layer and the jet-inflow. This periodicity appears to be the result of a helical precessing vortex core (PVC) present in that region of the combustor. The PVC has a precession frequency double (at about 570 Hz) that of the thermo-acoustic pulsation. A comparison of the various data sets suggests a strong coupling between the PVC and the thermo-acoustic pulsation in the noisy flame. Measurements of the quiet flame revealed a global fluctuation in both velocity and heat-release around 364 Hz but no clear evidence of a PVC.
C. Carter acknowledges support of the Air Force Office of Scientific Research (AFOSR) Windows on Europe Program. Figure 1a is reproduced with permission from Springer-Verlag—from Sustained multi-kHz flamefront and 3-component velocity-field measurements, by I. Boxx, M. Stöhr, C. Carter and W. Meier. Appl Phys B (2009) 95: 23–29. and from Elsevier Science—from Temporally resolved planar measurements of transient phenomena in a partially pre-mixed swirl flame in a gas turbine model combustor, by I. Boxx, M. Stöhr, C. Carter and W. Meier. Combustion and Flame, 157 (2009), 1,510–1,525. Figure 1b is reproduced with permission from Elsevier Science—from Detailed characterization of the dynamics of thermo-acoustic pulsations in a lean premixed swirl flame, by W. Meier, P. Weigand, X. R. Duan, R. Giezendanner-Thoben. Combustion and Flame 150 (2007) 2–26.