Design and Development Test of a Gas Turbine Combustor for High Hydrogen Medium Heating Value Syngas Fuel

2005 ◽  
Author(s):  
Gang Xu ◽  
Yufeng Cui ◽  
Bin Yu ◽  
Yu Lei ◽  
Chaoqun Nie ◽  
...  
Keyword(s):  
Temperature Profile ◽  
Gas Turbine ◽  
Coal Gasification ◽  
Three Dimensional ◽  
Engineering Thermophysics ◽  
Gas Turbine Combustor ◽  
High Hydrogen ◽  
Heating Value ◽  
Exhaust Temperature ◽  
Full Scale Tests

When gas turbine is used in coal co-production system, its combustor needs to burn syngas produced by coal gasification. The syngas’ main combustible compositions are CO and H2, and it has a nominal lower heating value of 10920kJ/ncm. In this paper, three modification schemes of a heavy-duty gas turbine combustor burning syngas are proposed. Flow fields, temperature profile and chemical reaction characteristics are compared using three-dimensional CFD numerical simulation and two of them have been chosen for medium-pressure, full-scale tests at the Gas Turbine Combustor Laboratory of the Institute of Engineering Thermophysics, Chinese Academy of Sciences. Laboratory tests show good result in exhaust emissions, combustor efficiency, exhaust temperature profile, and metal temperature distribution of liner and transaction pieces, which indicate that the retrofitting schemes satisfied the design specification. In addition, the dynamic characteristics of the combustors are researched applying FFT and wavelet analyses.

Three-Dimensional CFD Analysis of a Gas Turbine Combustor for Medium/Low Heating Value Syngas Fuel

2008 ◽  
Author(s):  
Yan Xiong ◽  
Lucheng Ji ◽  
Zhedian Zhang ◽  
Yue Wang ◽  
Yunhan Xiao
Keyword(s):  
Gas Turbine ◽  
Film Cooling ◽  
Coal Gasification ◽  
Stokes Equations ◽  
Three Dimensional ◽  
Combined Cycle ◽  
Gas Turbine Combustor ◽  
Integrated Gasification Combined Cycle ◽  
Heating Value ◽  
Flamelet Model

Gas turbine is one of the key components for integrated gasification combined cycle (IGCC) system. Combustor of the gas turbine needs to burn medium/low heating value syngas produced by coal gasification. In order to save time and cost during the design and development of a gas turbine combustor for medium/low heating value syngas, computational fluid dynamics (CFD) offers a good mean. In this paper, 3D numerical simulations were carried out on a full scale multi-nozzle gas turbine combustor using commercial CFD software FLUENT. A 72 degrees sector was modeled to minimize the number of cells of the grid. For the fluid flow part, viscous Navier-Stokes equations were solved. The realizable k-ε turbulence model was adopted. Steady laminar flamelet model was used for the reacting system. The interaction between fluid turbulence and combustion chemistry was taken into account by the PDF (probability density function) model. The simulation was performed with two design schemes which are head cooling using film-cooling and impingement cooling. The details of the flow field and temperature distribution inside the two gas turbine combustors obtained could be cited as references for design and retrofit. Similarities were found between the predicted and experimental data of the transition duct exit temperature profile. There is much work yet to be done on modeling validation in the future.

Calculations of Fuel NO Formation in a Gas Turbine Combustor

1991 ◽  
Author(s):  
Thomas J. Overcamp ◽  
Ajay K. Agrawal ◽  
Wei-Seng Cheng ◽  
Tah-Teh Yang
Keyword(s):  
Gas Turbine ◽  
Coal Gasification ◽  
Nitrogen Concentration ◽  
Experimental Studies ◽  
Three Dimensional ◽  
Two Dimensional ◽  
Gas Turbine Combustor ◽  
Nitrogen Inputs ◽  
Nitrogen Conversion ◽  
Three Dimensional Simulations

PCGC-2, a two-dimensional combustion code for pulverized coal gasification and combustion, and PHOENICS, a general purpose fluid dynamics code, were adapted for use in simulating the conversion of fuel nitrogen to nitric oxide, NO, in a gas turbine combustor using low-Btu fuel. A two-reaction global mechanism was used to describe the oxidation of fuel nitrogen. PCGC-2 is limited to two-dimensional, axisymmetric calculations. Both two- and three-dimensional simulations were made with PHOENICS. A parametric study was conducted to determine the variation of fuel nitrogen conversion with changes in the input variables including the inlet fuel nitrogen concentration and swirl numbers. The fuel nitrogen conversion predicted with both codes is similar to those reported in experimental studies on gaseous fuels. The conversion decreased with increasing fuel nitrogen inputs as shown in experimental data. The fuel conversion predicted in three-dimensional simulations for an industrial gas turbine was slightly higher than those in simplified two-dimensional simulations.

Acoustic Control of Dilution-Air Mixing in a Gas Turbine Combustor

1982 ◽  
Author(s):  
P. J. Vermeulen ◽  
J. Odgers ◽  
V. Ramesh
Keyword(s):  
Temperature Distribution ◽  
Temperature Profile ◽  
Gas Turbine ◽  
Exit Plane ◽  
Gas Turbine Combustor ◽  
Acoustic Control ◽  
Air Mixing ◽  
Air Flows ◽  
Plane Temperature ◽  
Load Conditions

A small combustor of normal design employing acoustic control of the dilution-air flows has been successfully tested up to “half-load” conditions. It has been shown that this technique can be used to selectively and progressively control the exit plane temperature distribution, and the ability to trim the temperature profile has been convincingly demonstrated. The acoustic driver power requirements were minimal indicating that driver power at “full-load” will not be excessive. The nature of the acoustically modulated dilution-air flows has been clearly establish to the design of combustors such that a desired exit plane temperature distribution may be achieved.

Three-Dimensional Computation of Gas Turbine Combustors and the Validation Studies of Turbulence and Combustion Models

1997 ◽  
Author(s):  
D. Biswas ◽  
K. Kawano ◽  
H. Iwasaki ◽  
M. Ishizuka ◽  
S. Yamanaka
Keyword(s):  
Gas Turbine ◽  
Validation Studies ◽  
Three Dimensional ◽  
Chemical Species ◽  
Reaction Rates ◽  
Reacting Flows ◽  
Gas Turbine Combustor ◽  
Combustion Models ◽  
Rate Of Dissipation

The main aim or the present work is to explore computational fluid dynamics and related turbulence and combustion models for application to the design, understanding and development of gas turbine combustor. Validation studies were conducted using the Semi-Implicit Method for Pressure Linked Equations (SIMPLE) scheme to solve the relevant steady, elliptical partial differential equations of the conservation of mass, momentum, energy and chemical species in three-dimensional cylindrical co-ordinate system to simulate the gas turbine combustion chamber configurations. A modified version of k-ε turbulence model was used for characterization of local turbulence in gas turbine combustor. Since, in the present study both diffusion and pre-mixed combustion were considered, in addition to familiar bi-molecular Arhenius relation, influence of turbulence on reaction rates was accounted for based on the eddy break up concept of Spalding and was assumed that the local reaction rate was proportional to the rate of dissipation of turbulent eddies. Firstly, the validity of the present approach with the turbulence and reaction models considered is checked by comparing the computed results with the standard experimental data on recirculation zone, mean axial velocity and temperature profiles, etc. for confined, reacting and non-reacting flows with reasonably well defined boundary conditions. Finally, the results of computation for practical gas turbine combustor using combined diffusion and pre-mixed combustion for different combustion conditions are discussed.

Thermoacoustic Modeling of a Gas Turbine Combustor Equipped With Acoustic Dampers

2005 ◽  
Vol 127 (2) ◽  
pp. 372-379 ◽  
Author(s):  
Valter Bellucci ◽  
Bruno Schuermans ◽  
Dariusz Nowak ◽  
Peter Flohr ◽  
Christian Oliver Paschereit
Keyword(s):  
Transfer Function ◽  
Gas Turbine ◽  
Mixture Fraction ◽  
Time Lag ◽  
Multiple Input Multiple Output ◽  
Three Dimensional ◽  
Analytical Models ◽  
Gas Turbine Combustor ◽  
Input Multiple Output ◽  
The Time Domain

In this work, the TA3 thermoacoustic network is presented and used to simulate acoustic pulsations occurring in a heavy-duty ALSTOM gas turbine. In our approach, the combustion system is represented as a network of acoustic elements corresponding to hood, burners, flames and combustor. The multi-burner arrangement is modeled by describing the hood and combustor as Multiple Input Multiple Output (MIMO) acoustic elements. The MIMO transfer function (linking acoustic pressures and acoustic velocities at burner locations) is obtained by a three-dimensional modal analysis performed with a Finite Element Method. Burner and flame analytical models are fitted to transfer function measurements. In particular, the flame transfer function model is based on the time-lag concept, where the phase shift between heat release and acoustic pressure depends on the time necessary for the mixture fraction (formed at the injector location) to be convected to the flame. By using a state-space approach, the time domain solution of the acoustic field is obtained. The nonlinearity limiting the pulsation amplitude growth is provided by a fuel saturation term. Furthermore, Helmholtz dampers applied to the gas turbine combustor are acoustically modeled and included in the TA3 model. Finally, the predicted noise reduction is compared to that achieved in the engine.

System Evaluation and LBTU Fuel Combustion Studies for IGCC Power Generation

1995 ◽  
Vol 117 (4) ◽  
pp. 673-677 ◽  
Author(s):  
C. S. Cook ◽  
J. C. Corman ◽  
D. M. Todd
Keyword(s):  
Gas Turbine ◽  
Gas Turbines ◽  
Coal Gasification ◽  
Flame Temperature ◽  
Combined Cycle ◽  
Gas Turbine Combustor ◽  
Gas Cleaning ◽  
Wide Range ◽  
Cycle Systems ◽  
Combined Cycles

The integration of gas turbines and combined cycle systems with advances in coal gasification and gas stream cleanup systems will result in economically viable IGCC systems. Optimization of IGCC systems for both emission levels and cost of electricity is critical to achieving this goal. A technical issue is the ability to use a wide range of coal and petroleum-based fuel gases in conventional gas turbine combustor hardware. In order to characterize the acceptability of these syngases for gas turbines, combustion studies were conducted with simulated coal gases using full-scale advanced gas turbine (7F) combustor components. It was found that NOx emissions could be correlated as a simple function of stoichiometric flame temperature for a wide range of heating values while CO emissions were shown to depend primarily on the H2 content of the fuel below heating values of 130 Btu/scf (5125 kJ/NM3) and for H2/CO ratios less than unity. The test program further demonstrated the capability of advanced can-annular combustion systems to burn fuels from air-blown gasifiers with fuel lower heating values as low as 90 Btu/scf (3548 kJ/NM3) at 2300°F (1260°C) firing temperature. In support of ongoing economic studies, numerous IGCC system evaluations have been conducted incorporating a majority of the commercial or near-commercial coal gasification systems coupled with “F” series gas turbine combined cycles. Both oxygen and air-blown configurations have been studied, in some cases with high and low-temperature gas cleaning systems. It has been shown that system studies must start with the characteristics and limitations of the gas turbine if output and operating economics are to be optimized throughout the range of ambient operating temperature and load variation.

Gas Turbine Combustor: Modelling and Optimization

2005 ◽  
Author(s):  
V. Ganesan ◽  
V. Jyothish Kumar
Keyword(s):  
Gas Turbine ◽  
Three Dimensional ◽  
Field Analysis ◽  
Gas Turbine Combustor ◽  
Cold Flow ◽  
Flow Losses ◽  
Flow Through ◽  
Flow Field Analysis ◽  
Probability Density Function Pdf ◽  
Modelling And Optimization

Present work is concerned with the flow field analysis inside an annular gas turbine combustor both under non-reacting and reacting conditions. Three-dimensional gas turbine combustor of 20-degree sector has been modeled using the pre-processor GAMBIT. Flow through the combustor has been simulated using FLUENT code by solving the appropriate governing equations viz., conservation of mass, momentum and energy. RNG κ-ε turbulence model is used for physical modeling. Initially prediffuser optimization has been carried out with respect to angle, length and contours. Flow through holes is modeled using porous jump boundary condition as well as modeling real holes themselves to study the efficacy of real hole modeling. Total pressure loss has been calculated to evaluate the cold flow as well as hot flow losses. Combustion has been modeled using the Probability Density Function (PDF) approach. Temperature and species concentrations are predicted.

Analysis of the Heat Transfer within combustor liners Using a Combined Monte Carlo and two-flux method

2021 ◽  
pp. 1-25
Author(s):  
Andressa Johnson ◽  
Xinyu Zhao
Keyword(s):  
Monte Carlo ◽  
Gas Turbine ◽  
Radiation Treatment ◽  
Three Dimensional ◽  
Radiative Energy ◽  
Gas Turbine Combustor ◽  
Eddy Simulation ◽  
Elevated Pressures ◽  
Large Eddy ◽  
Model Gas Turbine Combustor

Abstract One consequence of increasing efficiency of gas turbine combustors is higher temperatures within the combustor. Management of larger heat load has been advanced to protect the combustor wall and turbines, and among those are thermal barrier coatings (TBCs). Historically, both the flame and TBCs have received a simplified radiation treatment using effective absorptivities and emissivities. In this study, non-gray radiation is compared to gray and black radiation by combining three-dimensional Monte Carlo Ray Tracing solution of non-gray flames in a model gas turbine combustor to one-dimensional energy balance within combustor liners. A recent large eddy simulation of a gas turbine combustor is analyzed, where both gray and non-gray models are exercised. A two-band spectral model is employed for the TBC, where a translucent band and an opaque band are identified. A line-by-line treatment for gas-phase radiation is adopted, and the incident radiative energy on the combustor wall is collected using the MCRT solver, where the fraction of radiative energy within the translucent band is collected and compared with those obtained from the blackbody assumption. The temperature along the multi-layered combustor wall is computed and parametric comparison is conducted. The effects of the nongray flame radiation are more prominent at elevated pressures than at atmospheric pressure. The gray model is found to over-predict the TBC temperature, which leads to a difference of approximately 150 K in the prediction of peak temperature on the hot side of the TBC.

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