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.

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 Active Control Application to a Model Gas Turbine Combustor

1990 ◽  
Author(s):  
J. Brouwer ◽  
B. A. Ault ◽  
J. E. Bobrow ◽  
G. S. Samuelsen
Keyword(s):  
Feedback Control ◽  
Gas Turbine ◽  
Active Control ◽  
Input Parameter ◽  
Radiative Flux ◽  
Gas Turbine Combustor ◽  
Control Computer ◽  
Loop Feedback ◽  
Model Gas Turbine Combustor ◽  
Control Application

Closed-loop feedback control, developed in a axisymmetric can combustor, is demonstrated in a model can combustor with discrete wall jets. The study represents the initial steps toward the application of feedback control technology to practical gas turbine combustion systems. For the present application, the radiative flux from soot particulate is used as an indication of combustor performance, and nozzle atomizing air is selected as the input parameter. A measurement of radiative flux at the exit plane of the combustor is conveyed to a control computer which invokes an optimization algorithm to determine changes in the dome region necessary to minimize the radiative flux from soot. The results demonstrate the utility and potential of active control for maintaining optimal performance in real-time.

scholarly journals The Effect of Discrete Pilot Hydrogen Dopant Injection on the Lean Blowout Performance of a Model Gas Turbine Combustor

1999 ◽  
Author(s):  
Oanh Nguyen ◽  
Scott Samuelsen
Keyword(s):  
Gas Turbine ◽  
Atmospheric Pressure ◽  
Gas Turbines ◽  
Nox Emissions ◽  
Gas Turbine Combustor ◽  
Lean Blowout ◽  
Lean Combustion ◽  
Attractive Option ◽  
Overall Performance ◽  
Model Gas Turbine Combustor

In view of increasingly stringent NOx emissions regulations on stationary gas turbines, lean combustion offers an attractive option to reduce reaction temperatures and thereby decrease NOx production. Under lean operation, however, the reaction is vulnerable to blowout. It is herein postulated that pilot hydrogen dopant injection, discretely located, can enhance the lean blowout performance without sacrificing overall performance. The present study addresses this hypothesis in a research combustor assembly, operated at atmospheric pressure, and fired on natural gas using rapid mixing injection, typical of commercial units. Five hydrogen injector scenarios are investigated. The results show that (1) pilot hydrogen dopant injection, discretely located, leads to improved lean blowout performance and (2) the location of discrete injection has a significant impact on the effectiveness of the doping strategy.

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