Evaluation of Thermocouple and Thermal Radiation Instrumentation for Measuring Gas turbine Combustor Liner Wall Temperature

Thermal barrier coating (TBC) plays a vital role in the gas turbine combustor liner (CL) to mitigate the internal heat transfer from combustion gas to the CL and enhance the parent material lifetime of the CL. This present study examined the thermal analysis and creep lifetime prediction based on three different TBC thicknesses, 400, 800, and 1200 μm, coated on the inner CL using the coupled computational fluid dynamics/finite element method. The simulation method was divided into three models to minimize the amount of computational work involved. The Eddy Dissipation Model was used in the first model to simulate premixed methane-air combustion, and the wall temperature of the inner CL was obtained. The conjugate heat transfer simulation on the external cooling flows from the rib turbulator, impingement jet, and cross flow, and the wall temperature of the outer CL was obtained in the second model. The thermal analysis was carried out in the third model using three different TBC thicknesses and incorporating the wall data from the first and second model. The effect of increasing TBC thickness shows that the TBC surface temperature was increased. Thereby, the inner CL metal temperature was decreased due to the TBC thickness as well as the material properties of Yttria Stabilized Zirconia, which has low thermal conductivity and a high thermal expansion coefficient. With the increase in TBC thickness, the average temperature difference between the TBC surface and the inner metal surface increased. In contrast, the average temperature difference between the inner and outer metal surfaces remained nearly constant. The von Mises equivalent stress, based on the material property and thermal expansion coefficient, was determined and used to find the creep lifetime of the CL using the Larson–Miller rupture curve for all TBC thickness cases in order to analyze the thermo-structure. Except in the C-channel, the increasing TBC thickness was found to effectively increase the CL lifespan. Furthermore, the case without TBC was compared with the damaged CL with cracks due to thermal stress, which was prevented by increasing TBC thickness shown in this present study.

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Numerical Investigation of Gas Turbine Combustor Liner Film Cooling Slots

Volume 5C: Heat Transfer ◽

10.1115/gt2018-75608 ◽

2018 ◽

Author(s):

Firat Kiyici ◽

Ahmet Topal ◽

Ender Hepkaya ◽

Sinan Inanli

Keyword(s):

Heat Transfer ◽

Prandtl Number ◽

Surface Temperature ◽

Gas Turbine ◽

Film Cooling ◽

Turbulent Prandtl Number ◽

Surface Cooling ◽

Gas Turbine Combustor ◽

Cooling Effectiveness ◽

Combustor Liner

A numerical study, based on experimental work of Inanli et al. [1] is conducted to understand the heat transfer characteristics of film cooled test plates that represent the gas turbine combustor liner cooling system. Film cooling tests are conducted by six different slot geometries and they are scaled-up model of real combustor liner. Three different blowing ratios are applied to six different geometries and surface cooling effectiveness is determined for each test condition by measuring the surface temperature distribution. Effects of geometrical and flow parameters on cooling effectiveness are investigated. In this study, Conjugate Heat Transfer (CHT) simulations are performed with different turbulence models. Effect of the turbulent Prandtl Number is also investigated in terms of heat transfer distribution along the measurement surface. For this purpose, turbulent Prandtl number is calculated with a correlation as a function of local surface temperature gradient and its effect also compared with the constant turbulent Prandtl numbers. Good agreement is obtained with two-layered k–ϵ with modified Turbulent Prandtl number.

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Experimental Assessment of the Emissions Benefits of a Ceramic Gas Turbine Combustor

Volume 5: Manufacturing Materials and Metallurgy; Ceramics; Structures and Dynamics; Controls, Diagnostics and Instrumentation; Education; General ◽

10.1115/96-gt-318 ◽

1996 ◽

Cited By ~ 4

Author(s):

K. O. Smith ◽

A. Fahme

Keyword(s):

Natural Gas ◽

Gas Turbine ◽

Flow Distribution ◽

Operating Conditions ◽

Nox Emissions ◽

Fuel Injector ◽

Gas Turbine Combustor ◽

Experimental Assessment ◽

Industrial Gas Turbine ◽

Combustor Liner

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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Multi-fidelity modelling of an impingement/effusion cooled gas turbine combustor liner

Applied Thermal Engineering ◽

10.1016/j.applthermaleng.2020.116318 ◽

2020 ◽

pp. 116318

Author(s):

M.J. Yoko ◽

X. Sun ◽

S.J. van der Spuy ◽

V. Sethi

Keyword(s):

Gas Turbine ◽

Gas Turbine Combustor ◽

Combustor Liner

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Analysis of the influence of cooling hole arrangement on the protection of a gas turbine combustor liner

Meccanica ◽

10.1007/s11012-018-0824-4 ◽

2018 ◽

Vol 53 (9) ◽

pp. 2257-2271 ◽

Cited By ~ 1

Author(s):

Ahlem Ben Sik Ali ◽

Wassim Kriaa ◽

Hatem Mhiri ◽

Philippe Bournot

Keyword(s):

Gas Turbine ◽

Gas Turbine Combustor ◽

Cooling Hole ◽

Combustor Liner

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Wall Temperature Measurements in a Full-Scale Gas Turbine Combustor Test Rig With Fiber Coupled Phosphor Thermometry

Journal of Turbomachinery ◽

10.1115/1.4049104 ◽

2020 ◽

Vol 143 (1) ◽

Author(s):

Patrick Nau ◽

Simon Görs ◽

Christoph Arndt ◽

Benjamin Witzel ◽

Torsten Endres

Keyword(s):

High Pressure ◽

Gas Turbine ◽

Wall Temperature ◽

Clean Energy ◽

Full Scale ◽

Temperature Measurements ◽

Test Facility ◽

Fiber Optic Probe ◽

Gas Turbine Combustor ◽

Phosphor Thermometry

Abstract Wall temperature measurements with fiber coupled online phosphor thermometry were, for the first time, successfully performed in a full-scale H-class Siemens gas turbine combustor. Online wall temperatures were obtained during high-pressure combustion tests up to 8 bar at the Siemens Clean Energy Center (CEC) test facility. Since optical access to the combustion chamber with fibers being able to provide high laser energies is extremely challenging, we developed a custom-built measurement system consisting of a water-cooled fiber optic probe and a mobile measurement container. A suitable combination of chemical binder and thermographic phosphor was identified for temperatures up to 1800 K on combustor walls coated with a thermal barrier coating (TBC). To our knowledge, these are the first measurements reported with fiber coupled online phosphor thermometry in a full-scale high-pressure gas turbine combustor. Details of the setup and the measurement procedures will be presented. The measured signals were influenced by strong background emissions probably from CO*2 chemiluminescence. Strategies for correcting background emissions and data evaluation procedures are discussed. The presented measurement technique enables the detailed study of combustor wall temperatures and using this information an optimization of the gas turbine cooling design.

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CFD Modeling of a Gas Turbine Combustor From Compressor Exit to Turbine Inlet

Journal of Engineering for Gas Turbines and Power ◽

10.1115/1.2816318 ◽

1999 ◽

Vol 121 (1) ◽

pp. 89-95 ◽

Cited By ~ 18

Author(s):

D. S. Crocker ◽

D. Nickolaus ◽

C. E. Smith

Keyword(s):

Gas Turbine ◽

Coupled Model ◽

Design Tool ◽

Cfd Modeling ◽

Gas Turbine Combustor ◽

Strongly Coupled ◽

Gas Radiation ◽

Cfd Models ◽

Turbine Inlet ◽

Combustor Liner

Gas turbine combustor CFD modeling has become an important combustor design tool in the past few years, but CFD models are generally limited to the flow field inside the combustor liner or the diffuser/combustor annulus region. Although strongly coupled in reality, the two regions have rarely been coupled in CFD modeling. A CFD calculation for a full model combustor from compressor diffuser exit to turbine inlet is described. The coupled model accomplishes the following two main objectives: (1) implicit description of flow splits and flow conditions for openings into the combustor liner, and (2) prediction of liner wall temperatures. Conjugate heat transfer with nonluminous gas radiation (appropriate for lean, low emission combustors) is utilized to predict wall temperatures compared to the conventional approach of predicting only near wall gas temperatures. Remaining difficult issues such as generating the grid, modeling Swirled vane passages, and modeling effusion cooling are also discussed.

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CHARACTERISATIONS OF CHROMIUM CARBIDE-BASED COATED COMBUSTOR LINER FOR GAS TURBINES

Jurnal Teknologi ◽

10.11113/jt.v76.5790 ◽

2015 ◽

Vol 76 (10) ◽

Author(s):

Salmi Mohd Yunus ◽

Mariyam Jameelah Ghazali ◽

Wan Fathul Hakim W. Zamrib ◽

Ahmad Afiq Pauzi ◽

Shuib Husin

Keyword(s):

Gas Turbine ◽

Chromium Carbide ◽

Gas Turbines ◽

Normal Operation ◽

Gas Turbine Combustor ◽

Turbine Engine ◽

Surface Damages ◽

Wear Damage ◽

Combustor Liner ◽

Coating Hardness

A gas turbine combustor liner experienced visible surface damages during its normal operation of 8000 hours. Small amplitudes of vibration during the operation contributed to a surface degradation, mainly wear. A chromium-carbide based hard coating was deposited via plasma spray technique on the outer surface of a combustor liner of a gas turbine engine. It was found that after the operation, the coating hardness had increased more than 30% compared to its minimum initial hardness and reached up to 744 HV particularly in the crossfire tube collar mating areas. Comparison between the coated and the uncoated liners were carried out in order to show how much the wear scars have been minimized throughout the operation under severe temperature of approximately 1, 500°C. It was found that in this study the coating of chromium-carbide is capable to reduce the wear damage due to the work hardening effect of the liner and their mating surfaces.

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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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