Radiation and Smoke From the Gas Turbine Combustor Using Heavy Fuels

1983 ◽  
Vol 105 (1) ◽  
pp. 82-88 ◽  
Author(s):  
Y. S. H. Najjar ◽  
E. M. Goodger
Keyword(s):  
Gas Turbine ◽  
Hydrogen Content ◽  
Temperature Measurements ◽  
Fuel Oil ◽  
Aviation Fuel ◽  
Soot Concentration ◽  
Gas Oil ◽  
Gas Turbine Combustor ◽  
Residual Fuel Oil ◽  
Rate Of Increase

Broadening of aviation fuel specifications has been simulated using blends of gas oil and residual fuel oil. Radiation, smoke, and temperature measurements in an experimental combustor at various air pressure, inlet temperture, and air/fuel ratios showed a diminishing rate of increase of radiation with soot concentration and reduced sensitivity of smoke to fuel hydrogen content at higher combustor pressures.

scholarly journals Combustor Liner Temperature in the Gas Turbine Using Heavy Fuels

1982 ◽  
Author(s):  
Y. S. H. Najjar
Keyword(s):  
Gas Turbine ◽  
Temperature Measurements ◽  
Fuel Oil ◽  
Aviation Fuel ◽  
Gas Oil ◽  
Residual Fuel Oil ◽  
Temperature Parameter ◽  
Heavy Fuels ◽  
Combustor Liner

Broadening of aviation fuel specifications has been simulated with blends of gas oil and residual fuel oil. Radiation, smoke and temperature measurements in a developed experimental combustor at various air pressures, inlet temperatures and air-fuel ratios permit derivation of a non-dimensional temperature parameter showing good correlation with theory.

Effects of Fuel-Nozzle Configurations on Particulate-Matter Emissions From a Model Gas Turbine Combustor

2008 ◽  
Author(s):  
Tomohiro Asai ◽  
Hiromi Koizumi ◽  
Shohei Yoshida ◽  
Hiroshi Inoue
Keyword(s):  
Particulate Matter ◽  
Gas Turbine ◽  
Experimental Results ◽  
Fuel Oil ◽  
Gas Oil ◽  
High Concentration ◽  
Gas Turbine Combustor ◽  
Particulate Matter Emissions ◽  
Fuel Nozzle ◽  
Model Gas Turbine Combustor

The present paper describes particulate-matter (PM) emissions from a model gas turbine combustor at atmospheric pressure, focusing on the effects fuel-nozzle configurations have on PM emissions. In this experiment, three types of fuel nozzles were employed: standard, annular, and multi-type. The annular and multi-type were designed as low-PM-emission fuel nozzles, based on our preliminary experimental results using the standard nozzle. Gas oil and fuel oil containing 0.2 wt% of carbon residue were used as the test fuels. The PM concentrations and particle-size distributions were measured with an electrical low-pressure impactor. The experimental results revealed that the PM concentrations for the annular and multi-type were dramatically reduced compared with that for the standard nozzle, demonstrating their PM-reducing effect. We found that the high-concentration regions seemed to be formed by soot aggregation, from the spatial-profile measurements of PM emissions from gas oil combustion. The high-concentration regions for the low-PM-emission fuel nozzles were located further upstream and they were on a smaller scale than that for the standard nozzle. This suggests that their PM-reducing effect may be due to their upstream location and the smaller-scale of their high-concentration regions.

scholarly journals Radiative Heat Transfer From Gas Turbine Flames

1979 ◽  
Author(s):  
C. A. Ferguson ◽  
A. M. Mellor
Keyword(s):  
Heat Transfer ◽  
Heat Flux ◽  
Gas Turbine ◽  
Radiative Heat ◽  
Normal Component ◽  
Particle Analysis ◽  
Soot Concentration ◽  
Gas Turbine Combustor ◽  
Turbulent Fluctuations ◽  
Model Gas Turbine Combustor

Measurements have been made of the normal component of the radiative heat flux to the wall of a model gas turbine combustor with and without a mirrored background. Measurements have also been made of the centerline soot concentration. The data show that the heat flux correlated with the soot concentration but not universally, since JET A fuel yielded a different curve 1han DIESEL fuel. A theoretical analysis of the heat flux from a soot suspension was formulated. A criterion was established for the use of a small particle analysis. Finally, it is shown that there is no correspondence between theory and these experiments. It is speculated that turbulent fluctuations need to be modeled.

Assessing fuel spill risks in polar waters: Temporal dynamics and behaviour of hydrocarbons from Antarctic diesel, marine gas oil and residual fuel oil

2016 ◽  
Vol 110 (1) ◽  
pp. 343-353 ◽  
Author(s):  
Kathryn E. Brown ◽  
Catherine K. King ◽  
Konstantinos Kotzakoulakis ◽  
Simon C. George ◽  
Peter L. Harrison
Keyword(s):  
Temporal Dynamics ◽  
Fuel Oil ◽  
Gas Oil ◽  
Residual Fuel Oil

scholarly journals Wall Temperature Measurements in a Full-Scale Gas Turbine Combustor Test Rig With Fiber Coupled Phosphor Thermometry

2020 ◽  
Vol 143 (1) ◽  
Author(s):  
Patrick Nau ◽  
Simon Görs ◽  
Christoph Arndt ◽  
Benjamin Witzel ◽  
Torsten Endres
Keyword(s):  
High Pressure ◽  
Gas Turbine ◽  
Wall Temperature ◽  
Clean Energy ◽  
Full Scale ◽  
Temperature Measurements ◽  
Test Facility ◽  
Fiber Optic Probe ◽  
Gas Turbine Combustor ◽  
Phosphor Thermometry

Abstract Wall temperature measurements with fiber coupled online phosphor thermometry were, for the first time, successfully performed in a full-scale H-class Siemens gas turbine combustor. Online wall temperatures were obtained during high-pressure combustion tests up to 8 bar at the Siemens Clean Energy Center (CEC) test facility. Since optical access to the combustion chamber with fibers being able to provide high laser energies is extremely challenging, we developed a custom-built measurement system consisting of a water-cooled fiber optic probe and a mobile measurement container. A suitable combination of chemical binder and thermographic phosphor was identified for temperatures up to 1800 K on combustor walls coated with a thermal barrier coating (TBC). To our knowledge, these are the first measurements reported with fiber coupled online phosphor thermometry in a full-scale high-pressure gas turbine combustor. Details of the setup and the measurement procedures will be presented. The measured signals were influenced by strong background emissions probably from CO*2 chemiluminescence. Strategies for correcting background emissions and data evaluation procedures are discussed. The presented measurement technique enables the detailed study of combustor wall temperatures and using this information an optimization of the gas turbine cooling design.

Wavelength-Scanned Tunable Diode Laser Temperature Measurements in a Model Gas Turbine Combustor

AIAA Journal ◽  
2007 ◽  
Vol 45 (2) ◽  
pp. 420-425 ◽  
Author(s):  
Xin Zhou ◽  
Jay B. Jeffries ◽  
Ronald K. Hanson ◽  
Guoqiang Li ◽  
Ephraim J. Gutmark
Keyword(s):  
Gas Turbine ◽  
Diode Laser ◽  
Temperature Measurements ◽  
Tunable Diode Laser ◽  
Gas Turbine Combustor ◽  
Model Gas Turbine Combustor

scholarly journals Exhaust gas temperature measurements in diagnostic examination of naval gas turbine engines: Part II Unsteady processes

2011 ◽  
Vol 18 (3) ◽  
pp. 37-42 ◽  
Author(s):  
Zbigniew Korczewski
Keyword(s):  
Gas Turbine ◽  
Temperature Measurements ◽  
Turbine Engines ◽  
Flow Section ◽  
Exhaust Gas ◽  
Gas Turbine Engines ◽  
Gas Temperature ◽  
Rate Of Increase ◽  
Exhaust Gas Temperature ◽  
Unsteady Processes

Exhaust gas temperature measurements in diagnostic examination of naval gas turbine engines: Part II Unsteady processes The second part of the article presents the results of operating diagnostic tests of a two- and three-shaft engine with a separate power turbine during the start-up and acceleration of the rotor units. Attention was paid to key importance of the correctness of operation of the automatic engine load control system, the input for which, among other signals, is the rate of increase of the exhaust gas flow temperature. The article presents sample damages of the engine flow section which resulted from disturbed functioning of this system. The unsteady operation of the compressor during engine acceleration was the source of excessive increase of the exhaust gas temperature behind the combustion chamber and partial burning of the turbine blade tips.

Observations of Flame Behavior in a Laboratory-Scale Pre-Mixed Natural Gas/Air Gas Turbine Combustor From CARS Temperature Measurements

2002 ◽  
Author(s):  
Paul O. Hedman ◽  
Daniel V. Flores ◽  
Thomas H. Fletcher
Keyword(s):  
Natural Gas ◽  
Gas Turbine ◽  
Operating Conditions ◽  
Laboratory Scale ◽  
Temperature Measurements ◽  
Gas Temperature ◽  
Gas Turbine Combustor ◽  
Stable Flame ◽  
Gas Flame ◽  
Anti Stokes

This objective of this study was to obtain instantaneous gas temperature measurements using a coherent anti-Stokes Raman spectrometer (CARS) in a laboratory-scale, gas-turbine combustor (LSGTC) with a pre-mixed, swirl-stabilized, natural gas flame. These measurements complement PLIF measurements of OH radical, and LDA measurements of velocity which are presented in companion papers [1,2]. Gas temperature measurements were obtained at each of four operating conditions (high swirl and medium swirl at fuel equivalence ratios of 0.80 and 0.65). Results of mean and standard deviation measurements are included in this paper for all four test cases. Additionally, example probably density functions (PDF) for the gas temperature at the 40 mm, 60 mm, and 80 mm axial locations are presented for the for the high swirl (HS) φ = 0.80 case (most stable flame) and the medium swirl (MS) φ = 0.65 case (least stable flame).

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