Design and Development of a Porous Injector for Gaseous Fuels Injection in Gas Turbine Combustor PDF Download
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Author: Non Meeboon Publisher: ISBN: Category : Languages : en Pages : 113
Book Description
A novel porous injector is designed for injection of gaseous fuel in land based gas turbine combustors. The injector is tested at atmospheric conditions at Combustion Research Laboratory, University of Cincinnati. In the present study, seven injector configurations are tested for mixing quality, LBO limits and emissions. For mixing studies, the CO2 technique is adopted to evaluate the fuel-air mixing under atmospheric conditions of the porous injector. The experiments are carried out at 4% pressure drop condition across the injector. The CO2 concentrations are converted to fuel mass fractions for the comparison. A comparison between the top/bottom injections, center/no center injection and 7/30 micron porous tubes show that these configurations do not impact the fuel-air mixing distribution. PIV measurements are carried out in non-reacting as well reacting conditions. Velocity profiles are obtained at a 1%-4% pressure drop condition. The experiments are carried out with and without combustor. A weak outer recirculation zone is observed downstream of the injector in the combustor. The velocity profiles are same at the exit plane of the injector with and without combustor. The velocity decreases gradually along the combustor. The ignition and lean blow out limit are observed to increase as the pressure drop increases. The flame liftoff distance is found to increase as the pressure drop increases. The NO, CO, and O2 emissions are evaluated at the downstream of the porous injector at 6" from the entrance of the combustor. The results show that the NOx emissions are ~ 7 ppm @ 15% O2.
Author: Non Meeboon Publisher: ISBN: Category : Languages : en Pages : 113
Book Description
A novel porous injector is designed for injection of gaseous fuel in land based gas turbine combustors. The injector is tested at atmospheric conditions at Combustion Research Laboratory, University of Cincinnati. In the present study, seven injector configurations are tested for mixing quality, LBO limits and emissions. For mixing studies, the CO2 technique is adopted to evaluate the fuel-air mixing under atmospheric conditions of the porous injector. The experiments are carried out at 4% pressure drop condition across the injector. The CO2 concentrations are converted to fuel mass fractions for the comparison. A comparison between the top/bottom injections, center/no center injection and 7/30 micron porous tubes show that these configurations do not impact the fuel-air mixing distribution. PIV measurements are carried out in non-reacting as well reacting conditions. Velocity profiles are obtained at a 1%-4% pressure drop condition. The experiments are carried out with and without combustor. A weak outer recirculation zone is observed downstream of the injector in the combustor. The velocity profiles are same at the exit plane of the injector with and without combustor. The velocity decreases gradually along the combustor. The ignition and lean blow out limit are observed to increase as the pressure drop increases. The flame liftoff distance is found to increase as the pressure drop increases. The NO, CO, and O2 emissions are evaluated at the downstream of the porous injector at 6" from the entrance of the combustor. The results show that the NOx emissions are ~ 7 ppm @ 15% O2.
Author: John Ernest Stevenson Publisher: ISBN: Category : Fuel Languages : en Pages : 54
Book Description
A new liquid-fuel injector was designed for use in the atmospheric-pressure, model gas turbine combustor in Bucknell University's Combustion Research Laboratory during alternative fuel testing. The current liquid-fuel injector requires a higher-than-desired pressure drop and volumetric flow rate to provide proper atomization of liquid fuels. An air-blast atomizer type of fuel injector was chosen and an experiment utilizing water as the working fluid was performed on a variable-geometry prototype. Visualization of the spray pattern was achieved through photography and the pressure drop was measured as a function of the required operating parameters. Experimental correlations were used to estimate droplet sizes over flow conditions similar to that which would be experienced in the actual combustor. The results of this experiment were used to select the desired geometric parameters for the proposed final injector design and a CAD model was generated. Eventually, the new injector will be fabricated and tested to provide final validation of the design prior to use in the combustion test apparatus.
Author: Publisher: ISBN: Category : Languages : en Pages :
Book Description
Industrial gas turbines are primarily fueled with natural gas. However, changes in fuel cost and availability, and a desire to control carbon dioxide emissions, are creating pressure to utilize other fuels. There is an increased interest in the use of fuels from coal gasification, such as syngas and hydrogen, and renewable fuels, such as biogas and biodiesel. Current turbine fuel injectors have had years of development to optimize their performance with natural gas. The new fuels appearing on the horizon can have combustion properties that differ substantially from natural gas. Factors such as turbulent flame speed, heat content, autoignition characteristics, and range of flammability must be considered when evaluating injector performance. The low swirl injector utilizes a unique flame stabilization mechanism and is under development for gas turbine applications. Its design and mode of operation allow it to operate effectively over a wide range of conditions. Studies conducted at LBNL indicate that the LSI can operate on fuels with a wide range of flame speeds, including hydrogen. It can also utilize low heat content fuels, such as biogas and syngas. We will discuss the low swirl injector operating parameters, and how the LSC performs with various alternative fuels.
Author: Non Meeboon
Author: Non Meeboon
Author: B. C. Schlein
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Author: Robert R. Tacina
Author: John Ernest Stevenson
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Author: Defense Documentation Center (U.S.)