Investigation of the Degradation Behaviors of a Gas Turbine Burner made of an Inconel 738LC Superalloy

DLE (Dry Low Emission) technology is widely used in land based gas turbines due to the increasing demands on low NOx levels. One of the key aspects in DLE combustion is achieving a good fuel and air mixing where the desired flame temperature is achieved without too high levels of combustion instabilities. To experimentally study fuel and air mixing it is convenient to use water along with a tracer instead of air and fuel. In this study fuel and air mixing and flow field inside an industrial gas turbine burner fitted to a water rig has been studied experimentally and numerically. The Reynolds number is approximately 75000 and the amount of fuel tracer is scaled to represent real engine conditions. The fuel concentration in the rig is experimentally visualized using a fluorescing dye in the water passing through the fuel system of the burner and recorded using a laser along with a CCD (Charge Couple Device) camera. The flow and concentration field in the burner is numerically studied using both the scale resolving SAS (Scale Adaptive Simulation) method and the LES (Large Eddy Simulation) method as well as using a traditional two equation URANS (Unsteady Reynolds Average Navier Stokes) approach. The aim of this study is to explore the differences and similarities between the URANS, SAS and LES models when applied to industrial geometries as well as their capabilities to accurately predict relevant features of an industrial burner such as concentration and velocity profiles. Both steady and unsteady RANS along with a standard two equation turbulence model fail to accurately predict the concentration field within the burner, instead they predict a concentration field with too sharp gradients, regions with almost no fuel tracer as well as regions with far too high concentration of the fuel tracer. The SAS and LES approach both predict a more smooth time averaged concentration field with the main difference that the tracer profile predicted by the LES has smoother gradients as compared to the tracer profile predicted by the SAS. The concentration predictions by the SAS model is in reasonable agreement with the measured concentration fields while the agreement for the LES model is excellent. The LES shows stronger fluctuations in velocity over time as compared to both URANS and SAS which is due to the reduced amounts of eddy viscosity in the LES model as compared to both URANS and SAS. This study shows that numerical methods are capable of predicting both velocity and concentration in a gas turbine burner. It is clear that both time and scale resolved methods are required to accurately capture the flow features of this and probably most industrial DLE gas turbine burners.

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Monte Carlo Simulation for Radiative Transfer in a High-Pressure Industrial Gas Turbine Combustion Chamber

Volume 1: Aerospace Heat Transfer; Computational Heat Transfer; Education; Environmental Heat Transfer; Fire and Combustion Systems; Gas Turbine Heat Transfer; Heat Transfer in Electronic Equipment; Heat Transfer in Energy Systems ◽

10.1115/ht2017-4819 ◽

2017 ◽

Cited By ~ 2

Author(s):

Tao Ren ◽

Michael F. Modest ◽

Somesh Roy

Keyword(s):

Monte Carlo ◽

Gas Turbine ◽

Radiation Effects ◽

Swirling Flow ◽

Calculation Model ◽

Navier Stokes ◽

Combustion Model ◽

Stirred Reactor ◽

Industrial Gas Turbine ◽

Gas Turbine Burner

Radiative heat transfer is studied numerically for reacting swirling flow in an industrial gas turbine burner operating at a pressure of 15 bar. The reacting field characteristics are computed by Reynolds-averaged Navier-Stokes (RANS) equations using the k-ε model with the partially stirred reactor (PaSR) combustion model. The GRI-Mech 2.11 mechanism, which includes nitrogen chemistry, is used to demonstrate the the ability of reducing NOx emissions of the combustion system. A Photon Monte Carlo (PMC) method coupled with a line-by-line spectral model is employed to accurately account for the radiation effects. CO2, H2O and CO are assumed to be the only radiatively participating species and wall radiation is considered as well. Optically thin and PMC-gray models are also employed to show the differences between the simplest radiative calculation models and the most accurate radiative calculation model, i.e., PMC-LBL, for the gas turbine burner. It was found that radiation does not significantly alter the temperature level as well as CO2 and H2O concentrations. However, it has significant impacts on the NOx levels at downstream locations.

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Large Eddy Simulation of rich ammonia/hydrogen/air combustion in a gas turbine burner

International Journal of Hydrogen Energy ◽

10.1016/j.ijhydene.2021.09.164 ◽

2021 ◽

Author(s):

Kévin Bioche ◽

Laurent Bricteux ◽

Andrea Bertolino ◽

Alessandro Parente ◽

Julien Blondeau

Keyword(s):

Large Eddy Simulation ◽

Gas Turbine ◽

Eddy Simulation ◽

Large Eddy ◽

Gas Turbine Burner

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Effects of Thermal Barrier Coating and Cooling System on a Heat-Resisting Stainless Steel Ring Performance in a Gas Turbine Burner

Journal of Failure Analysis and Prevention ◽

10.1007/s11668-020-00983-x ◽

2020 ◽

Vol 20 (5) ◽

pp. 1765-1770

Author(s):

Aliakbar Fallah Sheykhlari ◽

Saeed Khani Moghanaki ◽

Safarali Khatir ◽

Meisam Khodabakhshi

Keyword(s):

Stainless Steel ◽

Gas Turbine ◽

Thermal Barrier Coating ◽

Cooling System ◽

Thermal Barrier ◽

Barrier Coating ◽

Stainless Steel Ring ◽

Gas Turbine Burner

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Development and combustion characterization of a novel twin-fluid fuel injector in a swirl-stabilized gas turbine burner operating on straight vegetable oil

Experimental Thermal and Fluid Science ◽

10.1016/j.expthermflusci.2018.11.014 ◽

2019 ◽

Vol 102 ◽

pp. 279-290 ◽

Cited By ~ 1

Author(s):

Oladapo S. Akinyemi ◽

Lulin Jiang

Keyword(s):

Gas Turbine ◽

Vegetable Oil ◽

Fuel Injector ◽

Straight Vegetable Oil ◽

Gas Turbine Burner

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Investigation of a pure hydrogen fueled gas turbine burner

International Journal of Hydrogen Energy ◽

10.1016/j.ijhydene.2017.02.104 ◽

2017 ◽

Vol 42 (15) ◽

pp. 10513-10523 ◽

Cited By ~ 25

Author(s):

Alessandro Cappelletti ◽

Francesco Martelli

Keyword(s):

Gas Turbine ◽

Pure Hydrogen ◽

Gas Turbine Burner

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Validation of Advanced Computational Methods for Determining Flame Transfer Functions in Gas Turbine Combustion Systems

Volume 2: Turbo Expo 2007 ◽

10.1115/gt2007-27267 ◽

2007 ◽

Cited By ~ 2

Author(s):

Krzysztof Kostrzewa ◽

Berthold Noll ◽

Manfred Aigner ◽

Joachim Lepers ◽

Werner Krebs ◽

...

Keyword(s):

System Identification ◽

Heat Release ◽

Gas Turbine ◽

Gas Turbines ◽

Transfer Functions ◽

Sound Waves ◽

Gas Turbine Combustion ◽

Combustion Systems ◽

Combustion Processes ◽

Gas Turbine Burner

The operation envelope of modern gas turbines is affected by thermoacoustically induced combustion oscillations. The understanding and development of active and passive means for their suppression is crucial for the design process and field introduction of new gas turbine combustion systems. Whereas the propagation of acoustic sound waves in gas turbine combustion systems has been well understood, the flame induced acoustic source terms are still a major topic of investigation. The dynamics of combustion processes can be analyzed by means of flame transfer functions which relate heat release fluctuations to velocity fluctuations caused by a flame. The purpose of this paper is to introduce and to validate a novel computational approach to reconstruct flame transfer functions based on unsteady excited RANS simulations and system identification. Resulting time series of velocity and heat release are then used to reconstruct the flame transfer function by application of a system identification method based on Wiener-Hopf formulation. CFD/SI approach has been applied to a typical gas turbine burner. 3D unsteady simulations have been performed and the flame transfer results have been validated by comparison to experimental data. In addition the method has been benchmarked to results obtained from sinusoidal excitations.

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