Correction: Numerical Simulation of Flow Distribution in a Realistic Gas Turbine Combustor

Three subscale, cylindrical combustors were rig tested on natural gas at typical industrial gas turbine operating conditions. The intent of the testing was to determine the effect of combustor liner cooling on NOx and CO emissions. In order of decreasing liner cooling, a metal louvre-cooled combustor, a metal effusion-cooled combustor, and a backside-cooled ceramic (CFCC) combustor were evaluated. The three combustors were tested using the same lean-premixed fuel injector. Testing showed that reduced liner cooling produced lower CO emissions as reaction quenching near the liner wall was reduced. A reduction in CO emissions allows a reoptimization of the combustor air flow distribution to yield lower NOx emissions.

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Numerical Simulation of the Non-Reactive and Reactive Flow in a Swirled Model Gas Turbine Combustor

10.2514/6.2013-2434 ◽

2013 ◽

Cited By ~ 1

Author(s):

Gilles Reichling ◽

Berthold Noll ◽

Manfred Aigner

Keyword(s):

Numerical Simulation ◽

Gas Turbine ◽

Reactive Flow ◽

Gas Turbine Combustor ◽

Model Gas Turbine Combustor

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Numerical simulation of a low-emission gas turbine combustor using KIVA-II

International Journal for Numerical Methods in Fluids ◽

10.1002/fld.1650150803 ◽

1992 ◽

Vol 15 (8) ◽

pp. 865-881 ◽

Cited By ~ 8

Author(s):

S. L. Yang ◽

R. Chen ◽

M. C. Cline ◽

H. L. Nguyen ◽

G. J. Micklow

Keyword(s):

Numerical Simulation ◽

Gas Turbine ◽

Gas Turbine Combustor ◽

Low Emission

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Numerical Simulation for the Preliminary Design of Fuel Flexible Stationary Gas Turbine Combustors Using Conventional and Alternative Fuels

Volume 3: Cycle Innovations; Education; Electric Power; Fans and Blowers; Industrial and Cogeneration ◽

10.1115/gt2012-69615 ◽

2012 ◽

Author(s):

Washington Orlando Irrazabal Bohorquez ◽

João Roberto Barbosa ◽

Rob Johan Maria Bastiaans ◽

Philip de Goey

Keyword(s):

Numerical Simulation ◽

Gas Turbine ◽

Gas Turbines ◽

Alternative Fuels ◽

High Efficiency ◽

Numerical Study ◽

Operating Conditions ◽

Pollutant Emissions ◽

Gas Turbine Combustor ◽

Primary Zone

Currently, high efficiency and low emissions are most important requisites for the design of modern gas turbines due to the strong environmental restrictions around the world. In the past years, alternative fuels have been considered for application in industrial gas turbines. Therefore, combustor performance, pollutant emissions and the ability to burn several fuels became of much concern and high priority has been given to the combustor design. This paper describes a methodology focused on the design of stationary gas turbines combustion chambers with the ability to efficiently burn conventional and alternative fuels. A simplified methodology is used for the calculations of the equilibrium temperature and chemical species in the primary zone of a gas turbine combustor. Direct fuel injection and diffusion flames, together with numerical methods like Newton-Raphson, LU Factorization and Lagrange Polynomials, are used for the calculations. Diesel, ethanol and methanol fuels were chosen for the numerical study. A computer code sequentially calculates the main geometry of the combustor. From the numerical simulation it is concluded that the basic gas turbine combustor geometry, for some operating conditions and burning diesel, ethanol or methanol, are of similar sizes, because the development of aerodynamic characteristics predominate over the thermochemical properties. It is worth to note that the type of fuel has a marked effect on the stability and combustion advancement in the combustor. This can be seen when the primary zone is analyzed under a steady-state operating condition. At full power, the pressure is 1.8 MPa and the temperature 1,000 K at the combustor inlet. Then, the equivalence ratios in the primary zone are 1.3933 (diesel), 1.4352 (ethanol) and 1.3977 (methanol) and the equilibrium temperatures for the same operating conditions are 2,809 K (diesel), 2,754 K (ethanol) and 2,702 K (methanol). This means that the combustor can reach similar flame stability conditions, whereas the combustion efficiency will require richer fuel/air mixtures of ethanol or methanol are burnt instead of diesel. Another important result from the numerical study is that the concentration of the main pollutants (CO, CO2, NO, NO2) is reduced when ethanol or methanol are burnt, in place of diesel.

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Development of a Small Gas Turbine Combustor With Airblast Atomizer

Volume 2: Coal, Biomass and Alternative Fuels; Combustion and Fuels ◽

10.1115/85-igt-10 ◽

1985 ◽

Author(s):

A. Hoshino ◽

T. Tatsumi ◽

H. Sone ◽

M. Shibata

Keyword(s):

Gas Turbine ◽

Output Power ◽

Air Flow ◽

Flow Distribution ◽

Performance Characteristics ◽

Carbon Deposit ◽

Gas Turbine Combustor

Kawasaki Heavy Industries, Ltd. has recently developed the S5 gas turbine at rated output power of 24 KW for use primarily in driving generators. This paper describes the engineering difficulties we experienced in developing the combustor for the small gas turbine, and its performance characteristics. Particular difficulties that confronted us in developing the combustor that uses the airblast atomizer are ignition, combustor lean flame out limit and carbon deposit. To work out these problems, we used a “click baffle” in the airblast atomizer, and optimized combustor configuration and air flow distribution as well.

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Experimental and Numerical Study of Heat Transfer in a Gas Turbine Combustor Liner

Journal of Engineering for Gas Turbines and Power ◽

10.1115/1.1615256 ◽

2003 ◽

Vol 125 (4) ◽

pp. 994-1002 ◽

Cited By ~ 22

Author(s):

J. C. Bailey ◽

J. Intile ◽

T. F. Fric ◽

A. K. Tolpadi ◽

N. V. Nirmalan ◽

...

Keyword(s):

Heat Transfer ◽

Gas Turbine ◽

Numerical Study ◽

Cross Flow ◽

Turbulence Models ◽

Flow Distribution ◽

Transfer Coefficients ◽

Gas Turbine Combustor ◽

Heat Transfer Coefficients ◽

Combustor Liner

Experiments and numerical simulations were conducted to understand the heat transfer characteristics of a stationary gas turbine combustor liner cooled by impingement jets and cross flow between the liner and sleeve. Heat transfer was also aided by trip-strip turbulators on the outside of the liner and in the flowsleeve downstream of the jets. The study was aimed at enhancing heat transfer and prolonging the life of the combustor liner components. The combustor liner and flow sleeve were simulated using a flat-plate rig. The geometry has been scaled from actual combustion geometry except for the curvature. The jet Reynolds number and the mass-velocity ratios between the jet and cross flow in the rig were matched with the corresponding combustor conditions. A steady-state liquid crystal technique was used to measure spatially resolved heat transfer coefficients for the geometric and flow conditions mentioned above. The heat transfer was measured both in the impingement region as well as over the turbulators. A numerical model of the combustor test rig was created that included the impingement holes and the turbulators. Using CFD, the flow distribution within the flow sleeve and the heat transfer coefficients on the liner were both predicted. Calculations were made by varying the turbulence models, numerical schemes, and the geometrical mesh. The results obtained were compared to the experimental data and recommendations have been made with regard to the best modeling approach for such liner-flow sleeve configurations.

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Feature-Parameter-Criterion for Predicting Lean Blowout Limit of Gas Turbine Combustor and Bluff Body Burner

Mathematical Problems in Engineering ◽

10.1155/2013/939234 ◽

2013 ◽

Vol 2013 ◽

pp. 1-17 ◽

Cited By ~ 1

Author(s):

Hongtao Zheng ◽

Zhibo Zhang ◽

Yajun Li ◽

Zhiming Li

Keyword(s):

Gas Turbine ◽

Bluff Body ◽

Flow Distribution ◽

Gas Turbine Combustor ◽

Experiment Data ◽

Lean Blowout ◽

Feature Parameter ◽

Computational Fluid Dynamics Cfd ◽

Mixture Velocity ◽

Good Agreement

Lean blowout (LBO) limit is one of the most important combustor parameters. A new method named Feature-Parameter-Criterion (FPC) for predicting LBO limit has been put forward in the present work. A computational fluid dynamics (CFD) software FLUENT has been used to simulate the process of LBO of gas turbine combustor and bluff body burner. And “M” flame has been proposed as the portent for predicting lean blowout of gas turbine combustor. Effects of flow velocity, air temperature, droplet averaged-diameter, and flow distribution between swirlers and primary holes on the LBO limit of gas turbine combustor have been researched by use of Feature-Parameter-Criterion in this paper. The effects of fuel air mixture velocity and different structures on bluff body LBO limit have also been analyzed in the present work by use of FPC. The results show that the simulation of LBO limit based on FPC is in good agreement with the experiment data (the errors are about 5%) and this method is reliable for engineering applications.

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Experimental and Numerical Study of Heat Transfer in a Gas Turbine Combustor Liner

Volume 3: Turbo Expo 2002, Parts A and B ◽

10.1115/gt2002-30183 ◽

2002 ◽

Cited By ~ 4

Author(s):

Jeremy C. Bailey ◽

John Intile ◽

Thomas F. Fric ◽

Anil K. Tolpadi ◽

Nirm V. Nirmalan ◽

...

Keyword(s):

Heat Transfer ◽

Gas Turbine ◽

Numerical Study ◽

Cross Flow ◽

Turbulence Models ◽

Flow Distribution ◽

Transfer Coefficients ◽

Gas Turbine Combustor ◽

Heat Transfer Coefficients ◽

Combustor Liner

Experiments and numerical simulations were conducted to understand the heat transfer characteristics of a stationary gas turbine combustor liner cooled by impingement jets and cross flow between the liner and sleeve. Heat transfer was also aided by trip-strip turbulators on the outside of the liner and in the flowsleeve downstream of the jets. The study was aimed at enhancing heat transfer and prolonging the life of the combustor liner components. The combustor liner and flow sleeve were simulated using a flat plate rig. The geometry has been scaled from actual combustion geometry except for the curvature. The jet Reynolds number and the mass-velocity ratios between the jet and cross flow in the rig were matched with the corresponding combustor conditions. A steady state liquid crystal technique was used to measure spatially resolved heat transfer coefficients for the geometric and flow conditions mentioned above. The heat transfer was measured both in the impingement region as well as over the turbulators. A numerical model of the combustor test rig was created that included the impingement holes and the turbulators. Using CFD, the flow distribution within the flow sleeve and the heat transfer coefficients on the liner were both predicted. Calculations were made by varying the turbulence models, numerical schemes, and the geometrical mesh. The results obtained were compared to the experimental data and recommendations have been made with regard to the best modeling approach for such liner-flow sleeve configurations.

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