Nonlinear modeling of unstable gas turbine combustor dynamics using experimental data

2000 ◽  
Author(s):  
Tim Lieuwen ◽  
Doh-Hyoung Lee
Keyword(s):  
Experimental Data ◽  
Gas Turbine ◽  
Nonlinear Modeling ◽  
Gas Turbine Combustor

scholarly journals Biomass/Coal Derived Gas Utilization in a Gas Turbine Combustor

1998 ◽  
Author(s):  
P. D. J. Hoppesteyn ◽  
J. Andries ◽  
K. R. G. Hein
Keyword(s):  
Experimental Data ◽  
Gas Turbine ◽  
Calorific Value ◽  
Two Dimensional ◽  
Dimensional Model ◽  
Gas Turbine Combustor ◽  
Cylindrical Chamber ◽  
Fuel Gas ◽  
Gas Utilization ◽  
Two Dimensional Model

Low calorific value fuel gas, obtained by pressurized fluidized bed gasification of coal/biomass mixtures, is combusted at 0.8 MPa with air or oxygen in a vertical cylindrical chamber (D = 0.28 m, L = 2.0 m). The fuel (T = 1060 K) and oxydizer (air at 350 K, oxygen at 460 K) are injected coaxially, resulting in an essentially axissymmetric flow pattern. Particles have been removed from the fuel gas stream by a cyclone, mounted between the gasifier and the combustor. A two-dimensional model, implemented in the CFD code FLUENT was developed for the calculation of temperatures, flow patterns and species concentrations throughout the combustor. The calculated results are compared with experimental data for two low calorific value fuel gas compositions and two oxidizer compositions at two axial combustor locations (X/L = 0.175 and X/L = 1). The results appear to justify further investigation of the applicability of the model to low calorific value fuel gas fired gas turbine combustors.

Experimental Investigation of the Flow Inside a Water Model of a Gas Turbine Combustor: Part 1—Mean and Turbulent Flowfield

1995 ◽  
Vol 117 (3) ◽  
pp. 450-458 ◽  
Author(s):  
J. J. McGuirk ◽  
J. M. L. M. Palma
Keyword(s):  
Experimental Data ◽  
Gas Turbine ◽  
Laser Doppler Velocimetry ◽  
Recirculation Zone ◽  
Water Model ◽  
Doppler Velocimetry ◽  
Flow Conditions ◽  
Gas Turbine Combustor ◽  
High Turbulence ◽  
The Mean

The present study examines the flow inside the water model of a gas turbine combustor, with the two main objectives of increasing the understanding of this type of flow and providing experimental data to assist the development of mathematical models. The main features of the geometry are the interaction between two rows of radially opposed jets penetrating a cross-flowing axial stream with and without swirl, providing a set of data of relevance to all flows containing these features. The results, obtained by laser Doppler velocimetry, showed that under the present flow conditions, the first row of jets penetrate almost radially into the combustor and split after impingement, giving rise to a region of high turbulence intensity and a toroidal recirculation zone in the head of the combustor. Part 1 discusses the mean and turbulent flowfield, and the detailed study of the region near the impingement of the first row of jets is presented in Part 2 of this paper.

A Generalized Presentation of Gas-Turbine Combustor Performance

1957 ◽  
Author(s):  
A. E. Noreen ◽  
W. T. Martin
Keyword(s):  
Experimental Data ◽  
Gas Turbine ◽  
Dimensional Analysis ◽  
Combustion Rate ◽  
Laminar Flame ◽  
Empirical Evaluation ◽  
Combustion Efficiency ◽  
Laminar Flame Speed ◽  
Gas Turbine Combustor ◽  
Stability Limits

Experimental data on stability limits and combustion efficiency of a 3-in-diam combustor using gaseous fuel are presented. These data have been correlated by an empirical evaluation of the results of a dimensional analysis. Theories are proposed, based upon the experimental data, regarding combustor-stabilization processes. Laminar flame speed was shown to be a satisfactory index of the influence of base combustion rate on combustor performance.

scholarly journals Experimental data regarding the effects of urea addition into liquid fuel to combustion enhancement of a low NOx gas turbine combustor

Data in Brief ◽  
2021 ◽  
Vol 34 ◽  
pp. 106702
Author(s):  
Maria Grazia De Giorgi ◽  
Giuseppe Ciccarella ◽  
Donato Fontanarosa ◽  
Elisa Pescini ◽  
Antonio Ficarella
Keyword(s):  
Experimental Data ◽  
Gas Turbine ◽  
Liquid Fuel ◽  
Gas Turbine Combustor ◽  
Combustion Enhancement ◽  
Urea Addition

scholarly journals Numerical Analysis of Turbulent Combustion in a Model Swirl Gas Turbine Combustor

2016 ◽  
Vol 2016 ◽  
pp. 1-12 ◽  
Author(s):  
Ali Cemal Benim ◽  
Sohail Iqbal ◽  
Franz Joos ◽  
Alexander Wiedermann
Keyword(s):  
Experimental Data ◽  
Natural Gas ◽  
Gas Turbine ◽  
Turbulence Model ◽  
Flue Gas ◽  
Numerical Study ◽  
Mixture Fraction ◽  
Gas Turbine Combustor ◽  
Flue Gas Recirculation ◽  
Gas Recirculation

Turbulent reacting flows in a generic swirl gas turbine combustor are investigated numerically. Turbulence is modelled by a URANS formulation in combination with the SST turbulence model, as the basic modelling approach. For comparison, URANS is applied also in combination with the RSM turbulence model to one of the investigated cases. For this case, LES is also used for turbulence modelling. For modelling turbulence-chemistry interaction, a laminar flamelet model is used, which is based on the mixture fraction and the reaction progress variable. This model is implemented in the open source CFD code OpenFOAM, which has been used as the basis for the present investigation. For validation purposes, predictions are compared with the measurements for a natural gas flame with external flue gas recirculation. A good agreement with the experimental data is observed. Subsequently, the numerical study is extended to syngas, for comparing its combustion behavior with that of natural gas. Here, the analysis is carried out for cases without external flue gas recirculation. The computational model is observed to provide a fair prediction of the experimental data and predict the increased flashback propensity of syngas.

Study of the Cold Flow Field of a Multi-Injection Combustor

2009 ◽  
Author(s):  
F. Wang ◽  
Y. Huang ◽  
T. Deng
Keyword(s):  
Experimental Data ◽  
Flow Field ◽  
Gas Turbine ◽  
Recirculation Zone ◽  
Turbulent Model ◽  
Gas Turbine Combustor ◽  
Cold Flow ◽  
Basic Work ◽  
Lining Structure ◽  
Recirculation Zones

Multi-injection combustor (MIC) could extend the steady working range of the whole combustor and reduce emissions therefore, so it is one of the Gas Turbine Combustor (GTC) design direction of future. The cold flow character of MIC is the basic work for MIC designers. Because of the low cost nowadays, the CFD method is a very suitable tool for it. Thus, firstly realizable k-epsilon turbulent model (RKE) and Reynolds stress turbulent model (RSM) were used to simulate the downstream flow field of a double radial swirl-cup amongst a simple tube, and the prediction results are compared with the experimental data which are gained by another researcher in Beihang University. The comparison between the experimental data and the CFD prediction results are shown that in most regions, the prediction results quite agree with the experimental data, and the max error of RKE model and RSM model is about 5% and 3% respectively. So the RKE model can be used for swirl-cup combustor simulation for its low computing cost. Then the RKE model is applied in a single swirl-cup gas turbine combustor and two kinds of multi-injection GTC flow field simulation. In the comparison between one single swirl-cup and nine arranged swirl-cups which all are in the same lining structure, each swirl-cup in MIC has a recirculation zone after its exit. Gradually, the recirculation zones mixed and united together in the downstream region. Finally, the recirculation zones structure turns to be similar to the structure in the single swirl-cup GTC after the primary combustion holes. In the other comparison between two kinds of lining structures which all are fixed with the same multi-injection head, the primary combustion holes affect flow field obviously. All the recirculation zones finished before the former primary combustion holes of the MIC without the primary combustion holes, and the separated recirculation zones form a new recirculation zone close to the primary holes for the MIC with primary holes. So the MIC design should combine with the real combustor lining structure to make a high performance for the whole combustor.

Lean Blowout Research in a Generic Gas Turbine Combustor With High Optical Access

1993 ◽  
Author(s):  
G. J. Sturgess ◽  
D. Shouse
Keyword(s):  
Experimental Data ◽  
Gas Turbine ◽  
Air Force ◽  
Operating Conditions ◽  
Test Facility ◽  
Turbine Engines ◽  
Flame Stability ◽  
Gas Turbine Engines ◽  
Gas Turbine Combustor ◽  
Lean Blowout

The U.S. Air Force is conducting a comprehensive research program aimed at improving the design and analysis capabilities for flame stability and lean blowout in the combustors of aircraft gas turbine engines. As part of this program, a simplified version of a generic gas turbine combustor is used. The intent is to provide an experimental data base against which lean blowout modeling might be evaluated and calibrated. The design features of the combustor and its instrumentation are highlighted, and the test facility is described. Lean blowout results for gaseous propane fuel are presented over a range of operating conditions at three different dome flow splits. Comparison of results with those of a simplified research combustor is also made. Lean blowout behavior is complex, so that simple phenomenological correlations of experimental data will not be general enough for use as design tools.

Numerical Investigation of Combustion Instabilities in a Single-Element Lean Direct Inject Combustor Using Flamelet Based Approaches

2020 ◽  
Vol 142 (9) ◽  
Author(s):  
Saurabh Sudhir Patwardhan ◽  
Pravin Nakod ◽  
Stefano Orsino ◽  
Carlo Arguinzoni
Keyword(s):  
Experimental Data ◽  
Gas Turbine ◽  
Direct Injection ◽  
Single Element ◽  
Combustion Instabilities ◽  
Gas Turbine Combustor ◽  
Combustion Dynamics ◽  
Lean Direct Injection ◽  
Combustion Models ◽  
Simulation Results

Abstract In this paper, high-fidelity large eddy simulations (LES) along with flamelet-based combustion models are assessed to predict combustion dynamics in low-emission gas turbine combustor. A model configuration of a single-element lean direct injection (LDI) combustor from Purdue University (Huang et al., 2014, “Combustion Dynamics Behavior in a Single-Element Lean Direct Injection (LDI) Gas Turbine Combustor,” 50th AIAA/ASME/SAE/ASEE Joint Propulsion Conference, Cleveland, OH, July 28–30.) is used for the validation of simulation results. Two combustion models based on the flamelet concept, i.e., steady diffusion flamelet (SDF) model and flamelet generated manifold (FGM) model are employed to predict combustion instabilities. Simulations are carried out for two equivalence ratios of φ = 0.6, and 0.4. The results in the form of mode shapes, peak to peak pressure amplitude and power spectrum density (PSD) are compared with the experimental data of Huang et al. (2014, “Combustion Dynamics Behavior in a Single-Element Lean Direct Injection (LDI) Gas Turbine Combustor,” 50th AIAA/ASME/SAE/ASEE Joint Propulsion Conference, Cleveland, OH, July 28–30.). The effect of variation in the time-step size hence acoustic courant number is studied. Further, two numerical solver options, i.e., pressure-based segregated solver and pressure-based coupled solver, are used to understand their effect on the solution convergence regarding the number of time-steps required to reach the limit cycle of the pressure oscillations. A truncated (half) domain simulation is performed by applying an appropriate acoustic impedance boundary condition at the truncated location. Overall, the simulation results compare well with the experimental data and trends are captured accurately in all simulations. It builds confidence in flamelet-based combustion models for the use in combustion instability modeling which is traditionally done using finite rate chemistry models based on reduced kinetics.

Simulation of the Heat Transfer in a Gas Turbine Combustor Fueled With Coal-Water Mixture: Part 2 — Model Predictions and Experimental Data

1986 ◽  
Author(s):  
Ihab H. Farag ◽  
Joseph L. Vaillancourt
Keyword(s):  
Heat Transfer ◽  
Experimental Data ◽  
Heat Flux ◽  
Gas Turbine ◽  
Transfer Rate ◽  
Water Mixture ◽  
Gas Turbine Combustor ◽  
Total Heat Transfer ◽  
Transfer Processes ◽  
Model Predictions

Data was obtained from the combustion of coal derived fuels in a 30 inch diameter, 4 foot long bench scale atmospheric unit fueled with CWF. The data is presented and compared with model predictions of ash, temperature, and mole fraction distributions. A computer model was developed to simulate the heat transfer processes taking place in a gas turbine combustor (GTC) burning a coal water fuel (CWF). It is to predict the species and temperature distribution, the heat flux patterns, and the contribution of both convection and radiation to the total heat transfer rate. This model was verified in part 1 of this paper.

A Numerical Study of Spray Injected in a Gas Turbine Lean Pre-Mixed Pre-Vaporized Combustor

2015 ◽  
Vol 32 (1) ◽  
Author(s):  
Amedeo Amoresano ◽  
Maria Cristina Cameretti ◽  
Raffaele Tuccillo
Keyword(s):  
Experimental Data ◽  
Gas Turbine ◽  
Numerical Study ◽  
Fluid Dynamic ◽  
Spray Parameters ◽  
Flow Conditions ◽  
Gas Turbine Combustor ◽  
Flow Solver ◽  
Combustion Simulation ◽  
Fuel Vapour

AbstractThe authors have performed a numerical study to investigate the spray evolution in a modern gas turbine combustor of the Lean Pre-Mixed Pre-vaporized type. The CFD tool is able to simulate the injection conditions, by isolating and studying some specific phenomena. The calculations have been performed by using a 3-D fluid dynamic code, the FLUENT flow solver, by choosing the injection models on the basis of a comparative analysis with some experimental data, in terms of droplet diameters, obtained by PDA technique.In a first phase of the investigation, the numerical simulation refers to non-evaporating flow conditions, in order to validate the estimation of the fundamental spray parameters. Next, the calculations employ boundary conditions close to those occurring in the actual combustor operation, in order to predict the fuel vapour distribution throughout the premixing chamber. The results obtained allow the authors to perform combustion simulation in the whole domain.

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