Experimental Analysis of Soot Formation and Oxidation in a Gas Turbine Model Combustor Using Laser Diagnostics

2011 ◽  
Vol 133 (12) ◽  
Author(s):  
Klaus Peter Geigle ◽  
Jochen Zerbs ◽  
Markus Köhler ◽  
Michael Stöhr ◽  
Wolfgang Meier
Keyword(s):  
Gas Turbine ◽  
Soot Formation ◽  
Laser Diagnostics ◽  
Stereoscopic Particle Image Velocimetry ◽  
Data Set ◽  
Laser Induced Incandescence ◽  
Partially Premixed Flame ◽  
Secondary Air ◽  
Anti Stokes ◽  
Turbine Model

Sooting ethylene/air flames were investigated experimentally in a dual swirl gas turbine model combustor with good optical access at atmospheric pressure. The goals of the investigations were a detailed characterization of the soot formation and oxidation processes under gas turbine relevant conditions and the establishment of a data base for the validation of numerical combustion simulations. The flow field was measured by stereoscopic particle image velocimetry, the soot volume fractions by laser-induced incandescence, the heat release by OH chemiluminescence imaging and the temperatures by coherent anti-Stokes Raman scattering. Two flames are compared: a fuel-rich partially premixed flame with moderate soot concentrations and a second one with the same parameters but additional injection of secondary air. Instantaneous as well as average distributions of the measured quantities are presented and discussed. The measured soot distributions exhibit a high temporal and spatial dynamic. This behavior correlates with broad temperature probability density functions. With injection of secondary air downstream of the flame zone the distributions change drastically. The data set, including PDFs of soot concentration, temperature and flow velocity, is unique in combining different laser diagnostics with a combustor exhibiting a more challenging geometry than existing validation experiments.

Experimental Analysis of Soot Formation and Oxidation in a Gas Turbine Model Combustor Using Laser Diagnostics

2011 ◽  
Author(s):  
Klaus Peter Geigle ◽  
Jochen Zerbs ◽  
Markus Ko¨hler ◽  
Michael Sto¨hr ◽  
Wolfgang Meier
Keyword(s):  
Gas Turbine ◽  
Soot Formation ◽  
Laser Diagnostics ◽  
Stereoscopic Particle Image Velocimetry ◽  
Data Set ◽  
Laser Induced Incandescence ◽  
Partially Premixed Flame ◽  
Secondary Air ◽  
Anti Stokes ◽  
Turbine Model

Sooting ethylene/air flames were investigated experimentally in a dual swirl gas turbine model combustor with good optical access at atmospheric pressure. The goals of the investigations were a detailed characterization of the soot formation and oxidation processes under gas turbine relevant conditions and the establishment of a data base for the validation of numerical combustion simulations. The flow field was measured by stereoscopic particle image velocimetry, the soot volume fractions by laser-induced incandescence, the heat release by OH chemiluminescence imaging and the temperatures by coherent anti-Stokes Raman scattering. Two flames are compared: a fuel-rich partially premixed flame with moderate soot concentrations and a second one with the same parameters but additional injection of secondary air. Instantaneous as well as average distributions of the measured quantities are presented and discussed. The measured soot distributions exhibit a high temporal and spatial dynamic. This behaviour correlates with broad temperature probability density functions. With injection of secondary air downstream of the flame zone the distributions change drastically. The data set, including PDFs of soot concentration, temperature and flow velocity, is unique in combining different laser diagnostics with a combustor exhibiting a more challenging geometry than existing validation experiments.

Investigation of Soot Formation and Oxidation in a High-Pressure Gas Turbine Model Combustor by Laser Techniques

2007 ◽  
Author(s):  
Oliver Lammel ◽  
Klaus Peter Geigle ◽  
Rainer Lu¨ckerath ◽  
Wolfgang Meier ◽  
Manfred Aigner
Keyword(s):  
Gas Turbine ◽  
Soot Formation ◽  
Thermal Power ◽  
Data Sets ◽  
Measuring Techniques ◽  
Laser Induced Incandescence ◽  
Flow Field Characteristics ◽  
Secondary Air ◽  
Cooling Air ◽  
Anti Stokes

Swirl-stabilized, non-premixed C2H4/air flames were investigated at pressures up to 9 bar in order to contribute to a better understanding of soot formation and oxidation under gas turbine like conditions. The flames had a thermal power of up to 45 kW and were confined by a squared combustion chamber with quartz windows. Secondary air could be injected into the post-flame zone to study the influence of cooling air on the oxidation of soot. The good optical access to the flame enabled the application of optical and laser measuring techniques. Temperatures were measured by coherent anti-Stokes Raman scattering (CARS) and soot concentrations by 2D laser induced incandescence (LII). The influence of the flow field characteristics, known from previous measurements in similar configurations, on the soot distributions is discussed. Furthermore, the effects of pressure, equivalence ratio and secondary oxidation air on the instantaneous and mean soot distributions were studied. All measurements were performed under well-defined and documented conditions, so that the data sets are suitable for the validation of numerical simulations.

Structure of the Velocity and Soot Concentration Fields of a Swirl Stabilized Turbulent Non-Premixed Flame in a Gas Turbine Model Combustor

2014 ◽  
Author(s):  
Sandipan Chatterjee ◽  
Christopher Halmo ◽  
Ömer L. Gülder
Keyword(s):  
Flow Field ◽  
Gas Turbine ◽  
Strong Dependence ◽  
Field Measurements ◽  
Combustion Products ◽  
Stereoscopic Particle Image Velocimetry ◽  
Soot Concentration ◽  
Volume Fractions ◽  
Laser Induced Incandescence ◽  
Turbine Model

Turbulent non-premixed swirl flames were investigated in a gas turbine model combustor with optical access. Velocity and soot concentration fields for ethylene/air combustion at three overall fuel-air equivalence ratios, 0.222, 0.209 and 0.198, were studied. Stereoscopic particle image velocimetry measurements were used to study the flow field in the combustor, and time-averaged soot volume fractions were obtained using laser induced incandescence. The flow field and soot measurements were performed separately, but under identical conditions. The flow field measurements captured the inner and outer recirculation zones, the boundaries of which showed high turbulence intensity. This high intensity turbulence implies a rapid mixing of the cold reactants with the recirculating hot combustion products and chemically active radicals near the recirculation zone boundaries. The soot volume fractions showed a strong dependence on the overall fuel-air equivalence ratio. Regions of maximum soot had a conical shape and grew radially outward with downstream locations.

scholarly journals High-speed laser diagnostics for the study of flame dynamics in a lean premixed gas turbine model combustor

2010 ◽  
Vol 52 (3) ◽  
pp. 555-567 ◽  
Author(s):  
Isaac Boxx ◽  
Christoph M. Arndt ◽  
Campbell D. Carter ◽  
Wolfgang Meier
Keyword(s):  
Gas Turbine ◽  
High Speed ◽  
Laser Diagnostics ◽  
Flame Dynamics ◽  
Lean Premixed ◽  
Turbine Model

An Investigation of the Effects of Fuel Staging on Flame Structure in a Gas Turbine Model Combustor

2013 ◽  
Author(s):  
J. D. Gounder ◽  
I. Boxx ◽  
P. Kutne ◽  
F. Biagioli ◽  
H. Luebcke
Keyword(s):  
Gas Turbine ◽  
High Speed ◽  
Equivalence Ratio ◽  
Fuel Injection ◽  
Laser Diagnostics ◽  
Thermal Power ◽  
Flame Structure ◽  
Operating Conditions ◽  
Fuel Staging ◽  
Turbine Model

Gas turbine (GT) flames at lean operating conditions are susceptible to instabilities that can lead to unsteady operation, flame extinction, and thermoacoustic oscillations. High speed (10 kHz) laser and optical diagnostic techniques have been used to investigate the effect of fuel staging on the mechanisms involved in such instabilities and the overall performance of a gas turbine model combustor. The GT burner used in this study consists of coaxial swirlers which allow for fuel staging capability, where the fuel is varied from 100% to 20% fuel injection in the inner swirler. The burner is equipped with a combustion chamber with large quartz windows, allowing for the application of optical and laser diagnostics. Simultaneous high speed OH Planar Laser Induced Fluorescence (PLIF) and OH* chemiluminescence (CL) imaging, exhaust gas sampling and acoustic measurements were applied to characterize the flames and determine the operability limits of the combustor. Methane air flames at atmospheric pressure have been investigated at a constant thermal power of 58 kW. The global equivalence ratio was kept constant, while the fuel staging was varied. The bulk flow velocity at the exit plane was kept constant at 20 m/s. Simultaneous high speed particle image velocity (PIV) and OH PLIF measurements were performed at a repetition rate of 10 kHz on specifically chosen flames with a fixed staging and equivalence ratio. This paper will present the flame and the flow field structure resolved using the kHz measurement technique. The interaction between the velocity field and the flame front marked by the OH LIF will be presented. The mean PIV image provides the location of the inner and outer recirculation zones. The flame structure presented in this paper will also show the effectiveness of fuel mixing as the staging is varied. The changes in flame shape with variation in fuel staging is determined using the OH* chemiluminescence images. As the fuel flow in the inner swirler is reduced, the NOx and CO emissions also reduce and reach a minimum at a staging of 45% fuel being injected in the inner swirler. As fuel injection in the outer swirler increases beyond 60% the NOx and CO emissions start also increasing.

scholarly journals Chirped probe pulse femtosecond coherent anti-Stokes Raman scattering thermometry at 5 kHz in a Gas Turbine Model Combustor

2015 ◽  
Vol 35 (3) ◽  
pp. 3731-3738 ◽  
Author(s):  
Claresta N. Dennis ◽  
Carson D. Slabaugh ◽  
Isaac G. Boxx ◽  
Wolfgang Meier ◽  
Robert P. Lucht
Keyword(s):  
Raman Scattering ◽  
Gas Turbine ◽  
Probe Pulse ◽  
Anti Stokes ◽  
Turbine Model
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