Relevant bibliographies by topics / Gas-turbine flame analysis

Academic literature on the topic 'Gas-turbine flame analysis'

Author: Grafiati
Published: 10 December 2022
Last updated: 19 February 2023

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Journal articles on the topic "Gas-turbine flame analysis"

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Mohammad Nurizat Rahman, Norshakina Shahril, and Suzana Yusup. "Hydrogen-Enriched Natural Gas Swirling Flame Characteristics: A Numerical Analysis." CFD Letters 14, no. 7 (July 17, 2022): 100–112. http://dx.doi.org/10.37934/cfdl.14.7.100112.

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Increasing the amount of hydrogen (H2) in natural gas mixtures contributes to gas turbine (GT) decarbonisation initiatives. Hence, the swirling flame characteristics of natural gas mixtures with H2 are investigated in the current work using a numerical assessment of a single swirl burner, which is extensively employed in GT combustors. The baseline numerical and experimental cases pertained to natural gas compositions largely consisting of methane (CH4). The results show that the numerical model adequately describes the swirling component of the flame observed in the experiment. Altogether, the findings show that hydroxyl (OH) radical levels increase in H2-enriched CH4 flames, implying that greater OH pools are responsible for the change in flame structure caused by considerable H2 addition. The addition of 10 % H2 is predicted to raise the peak flame temperature by 4 % compared to the baseline CH4 flame. Therefore, adding 10 % H2 into a GT combustor without any flowrate tuning raises the risk of turbine material deterioration and increased thermal NOx emission. Due to the lower volumetric Lower Heating Value (LHV) of H2, which needs a higher volumetric fuel flow rate than burning natural gas/CH4 at the same thermal output, the addition of 2 % H2 is predicted to reduce the peak flame temperature by 4 % compared to the baseline CH4 flame. Hence, if 2 % H2 is fed into a GT combustor without any flowrate tuning, the required load may not be obtained. When compared to the baseline CH4 case, the addition of 5 % H2 is predicted to provide almost identical peak flame temperature, which can be postulated that the addition of 5 % H2 can produce roughly the same peak flame temperature as the pure CH4 flame because the Wobbe Index is comparable. Therefore, it reveals that incorporating 5 % H2 in the natural gas-fired GT combustor with nearly no modification is viable. More research, however, is required to fully capture the flame structure and strain for assessing transient-related phenomena such as flashback and blow off by raising the H2 proportion and utilising a higher precision turbulence model.
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Fadhil, Siti Sarah Ain, Hasril Hasini, Mohd Nasharuddin Mohd Jaafar, and Nor Fadzilah Othman. "Temperature Distribution Analysis on Syngas Combustion in Microgas Turbine." Applied Mechanics and Materials 819 (January 2016): 282–86. http://dx.doi.org/10.4028/www.scientific.net/amm.819.282.

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Gas turbines are capable to utlize variety of fuel including natural gas, fuel oils and synthetic gas. It has environmental advantages and thus gas turbines are favourable in the power generating industries. The use of synthetic gas or syngas may reduce the CO2 and NOx emissions. The efficiency of syngas is comparable with natural gas. With the current constrain on the environmental issues, the use of syngas in gas turbines has been increasing. Despite its many advantages, the study on the combustion characteristics still remains a challenge, due to its variety fuel components. This paper aims to discuss the CFD analysis on the flame and flue gas temperature distribution in a full scale microgas turbine operating on syngas. Three cases were simulated with variety of natural gas concentration. A base case firing natural gas (100% methane) was first established using actual operation. Validation on the combustion model is made by comparing the flame temperature distribution of methane with reasonable accuracy. Simulation results with syngas show similar flame temperature distribution as natural gas combustion. The average temperature is much dependent on the composition of methane in syngas. The highest temperature given by syngas is made from the highest methane composiotion.
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Wang, Cheng Jun, Xin Xin, Ping Jiang, and Wen Zeng. "Analysis of Fuel Properties Effects on Flame Radiation in a Gas Turbine Combustor." Applied Mechanics and Materials 385-386 (August 2013): 196–99. http://dx.doi.org/10.4028/www.scientific.net/amm.385-386.196.

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The influence of fuel properties on flame radiation transfer was investigated with numerical method under certain combustor fuel-air ratio and inlet air temperature in a gas turbine combustor. The numerical results show that the fuel properties affected the fuel pulverization quality, evaporation efficiency and combustion efficiency, which caused the flame temperature and its distribution change. Meanwhile, it has an effect on the formation and concentration distribution of soot, resulting in the changes of inner flame radiation heat flux and temperature caused by flame emitting radiation. Furthermore, the gas temperature change caused by the fuel properties more but the hydrogen content effect is relatively small, has an influence on the generation of NO which caused the change of the combustion efficiency.
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Bellucci, Valter, Bruno Schuermans, Dariusz Nowak, Peter Flohr, and Christian Oliver Paschereit. "Thermoacoustic Modeling of a Gas Turbine Combustor Equipped With Acoustic Dampers." Journal of Turbomachinery 127, no. 2 (April 1, 2005): 372–79. http://dx.doi.org/10.1115/1.1791284.

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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.
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Kim, Daesik, Sa Ryang Kim, and Kyu Tae Kim. "Thermoacoustic Analysis Considering Flame Location in a Gas Turbine Combustor." Journal of the Korean Society of Combustion 18, no. 1 (March 31, 2013): 1–6. http://dx.doi.org/10.15231/jksc.2013.18.1.001.

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Winkler, Dieter, Weiqun Geng, Geoffrey Engelbrecht, Peter Stuber, Klaus Knapp, and Timothy Griffin. "Staged combustion concept for gas turbines." Journal of the Global Power and Propulsion Society 1 (September 27, 2017): CVLCX0. http://dx.doi.org/10.22261/cvlcx0.

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AbstractGas turbine power plants with high load flexibility are particularly suitable to compensate power fluctuations of wind and solar plants. Conventional gas turbines suffer from higher emissions at low load operation. With the objective of improving this situation a staged combustion system has been investigated. At low gas turbine load an upstream stage (first stage) provides stable combustion at low emissions while at higher loads the downstream stage (second stage) is started to supplement the power. Three injection geometries have been studied by means of computational fluid dynamics (CFD) simulations and atmospheric tests. The investigated geometries were a simple annular gap, a jet-in-cross-flow configuration and a lobe mixer. With CFD simulations the quality of mixing of second stage fresh gas with first stage exhaust gas was assessed. The lobe mixer showed the best mixing quality and hence was expected to also be the best variant in terms of combustion. However atmospheric combustion tests showed lower emissions for the jet-in-cross-flow configuration. Comparing flame photos in the visible and ultraviolet (UV) range suggest that the flame might be lifted off for the lobe mixer, leading to insufficient time for carbon monoxide (CO) burnout. CFD analysis of turbulent flame speed, turbulence and strain rates support the hypotheses of lifted off flame. Overall the staged concept was found to show very promising results not only with natural gas but also with natural gas enriched with propane or hydrogen. The investigations showed that apart from having an efficient and compact mixing of the two stages it is also very important to design the flow field such that the second flame can be anchored properly in order to achieve compact flames with sufficient time for CO burnout.
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Hasini, Hasril, Norshah Hafeez Shuaib, and Wan Ahmad Fahmi Wan Abdullah. "CFD Analysis of Temperature Distribution in Can-Type Combustor Firing Synthetic Gas." Applied Mechanics and Materials 393 (September 2013): 741–46. http://dx.doi.org/10.4028/www.scientific.net/amm.393.741.

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This paper presents CFD analysis of the effect of syngas combustion in a full scale gas turbine combustor with specific emphasis given to the flame and flue gas temperature distribution. A base case solution was first established using conventional natural gas combustion. Actual operating boundary conditions such as swirl, diffusion and fuel mass flow were imposed on the model. The simulation result is validated with the flame temperature of typical natural gas combustion. Result from flow and combustion calculation shows reasonable trend of the swirl mixing effect. The maximum flame temperature was found to be the highest for syngas with the highest H2/CO ratio. However, the flue gas temperature was found to be approximately identical for all cases. The prediction of temperature distribution in the combustor would enable further estimation of pollutant species such as CO2and NOxin complex regions within the combustor.
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Dulin, Vladimir, Leonid Chikishev, Dmitriy Sharaborin, Aleksei Lobasov, Roman Tolstoguzov, Zundi Liu, Xiaoxiang Shi, Yuyang Li, and Dmitriy Markovich. "On the Flow Structure and Dynamics of Methane and Syngas Lean Flames in a Model Gas-Turbine Combustor." Energies 14, no. 24 (December 8, 2021): 8267. http://dx.doi.org/10.3390/en14248267.

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The present paper compares the flow structure and flame dynamics during combustion of methane and syngas in a model gas-turbine swirl burner. The burner is based on a design by Turbomeca. The fuel is supplied through injection holes between the swirler blades to provide well-premixed combustion, or fed as a central jet from the swirler’s centerbody to increase flame stability via a pilot flame. The measurements of flow structure and flame front are performed by using the stereo particle image velocimetry and OH planar laser-induced fluorescence methods. The measurements are performed for the atmospheric pressure without preheating and for 2 atm with the air preheated up to 500 K. The flow Reynolds numbers for the non-reacting flows at these two conditions are 1.5 × 103 and 1.0 × 103, respectively. The flame dynamics are analyzed based on a high-speed OH* chemiluminescence imaging. It is found that the flame dynamics at elevated conditions are related with frequent events of flame lift-off and global extinction, followed by re-ignition. The analysis of flow structure via the proper orthogonal decomposition reveals the presence of two different types of coherent flow fluctuations, namely, longitudinal and transverse instability modes. The same procedure is applied to the chemiluminescence images for visualization of bulk movement of the flame front and similar spatial structures are observed. Thus, the longitudinal and transverse instability modes are found in all cases, but for the syngas at the elevated pressure and temperature the longitudinal mode is related to strong thermoacoustic fluctuations. Therefore, the present study demonstrates that a lean syngas flame can become unstable at elevated pressure and temperature conditions due to a greater flame propagation speed, which results in periodic events of flame flash-back, extinction and re-ignition. The reported data is also useful for the validation of numerical simulation codes for syngas flames.
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Kuznetsov, Borys, Andrii Diadechko, Viktor Hudyma, Ihor Ovcharenko, Oleksandr Yaroshenko, Oleksandr Sampir, Yana Horbachova, and Mariia Tsurkan. "Numerical research of flame propagation conditions in narrow channels using the technology of thermal impulse treatment of turbine blades." Strength of Materials and Theory of Structures, no. 107 (October 29, 2021): 236–46. http://dx.doi.org/10.32347/2410-2547.2021.107.236-246.

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The analysis of the main modern trends in the development of views on the issue of cleaning of the cooling channels of turbine blades in gas turbine engines in the process of manufacture and repair at military repair enterprises has been carried out; the usage of the method of thermo impulse treatment with detonating gas mixtures for cleaning of the cooling channels of turbine blades in gas turbine engines is proposed. Cleaning the cooling channels of turbine blades of modern gas turbine engines is one of the most complex processes in their manufacture and repair. At the manufacturing stage, the cleaning process is necessary to remove microparticles of ceramics and cutting chip that are produced during the formation of the output edges of the cooling.
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Rahman, Mohammad Nurizat, Norshakina Shahril, Suzana Yusup, and Ismail Shariff. "Hydrogen Co-Firing Characteristics in a Single Swirl Burner: A Numerical Analysis." IOP Conference Series: Materials Science and Engineering 1257, no. 1 (October 1, 2022): 012020. http://dx.doi.org/10.1088/1757-899x/1257/1/012020.

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Abstract Hydrogen is gaining traction as an energy carrier in the decarbonisation and net-zero-emissions agenda. Because hydrogen is a clean energy carrier, increasing the percentage of hydrogen in natural gas mixtures aids in the decarbonisation initiatives. Hence, the flame characteristics of the natural gas mixtures, together with hydrogen are explored in the current study through a numerical assessment of a single swirl burner (swirl number, SN 0.78) since the said burner is widely used in gas turbine (GT) combustors. The baseline CFD and experimental cases referred to natural gas compositions primarily composed of methane (CH4). The results reveal that the CFD model can effectively represent the swirling component of the flame as seen in the experiment. A 5% hydrogen addition had virtually no effect on the swirling flame structure, as shown by qualitative evaluation of hydroxyl (OH) behaviour and flame temperature in comparison to the baseline methane flame. Despite this, the addition of hydrogen has increased the OH radical pool during combustion, causing a small change in flame temperature. Overall, the novelty of the current research is the opportunity to fire 5% hydrogen in a CH4-dominated GT combustor without any major retrofitting operations, as the study discovered that 5% hydrogen in a pure CH4 stream has a minor affect. However, more research is needed to properly capture the flame structure and strain for assessing transient-related phenomena like flashback and blow off by increasing the hydrogen proportion and using a higher accuracy turbulence model.
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Dissertations / Theses on the topic "Gas-turbine flame analysis"

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Sampathkumar, Shrihari. "Thermoacoustic Analysis and Experimental Validation of Statistically-Based Flame Transfer Function Extracted from Computational Fluid Dynamics." Thesis, Virginia Tech, 2019. http://hdl.handle.net/10919/101897.

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Thermoacoustic instabilities arise and sustain due to the coupling of unsteady heat release from the flame and the acoustic field. One potential driving mechanism for these instabilities arise when velocity fluctuations (u') at the fuel injection location causes perturbations in the local equivalence ratio and is convected to the flame location generating an unsteady heat release (q') at a particular convection time delay, τ. Physically, τ is the time for the fuel to convect from injection to the flame. The n-τ Flame Transfer Function (FTF) is commonly used to model this relationship assuming an infinitesimally thin flame with a fixed τ. In practical systems, complex swirling flows, multiple fuel injections points, and recirculation zones create a distribution of τ, which can vary widely making a statistical description more representative. Furthermore, increased flame lengths and higher frequency instabilities with short acoustic wavelengths challenge the 'thin-flame' approximation. The present study outlines a methodology of using distributed convective fuel time delays and heat release rates in a one-dimensional (1-D) linear stability model based on the transfer matrix approach. CFD analyses, with the Flamelet Generated Manifold (FGM) combustion model are performed and probability density functions (PDFs) of the convective time delay and local heat release rates are extracted. These are then used as inputs to the 1-D Thermoacoustic model. Results are compared with the experimental results, and the proposed methodology improves the accuracy of stability predictions of 1-D Thermoacoustic modeling.
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(14042402), Paul K. Hannah. "Data-fusion, self-organizing continuous maps, and eigenflames applied to modeling, control and visualization." Thesis, 2005. https://figshare.com/articles/thesis/Data-fusion_self-organizing_continuous_maps_and_eigenflames_applied_to_modeling_control_and_visualization/21454035.

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In this thesis a new Data-Fusion framework is presented. An object-oriented approach to neural network programming is considered, and the approach is used to develop the Self-Organizing Continuous Map, a family of neural networks based upon the self-organizing feature map. eigenflame and tomographic techniques are used for gas-turbine flame analysis.

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Books on the topic "Gas-turbine flame analysis"

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R, Hicks Y., and United States. National Aeronautics and Space Administration., eds. Imaging fluorescent combustion species in gas turbine flame tubes: On complexities in real systems. [Washington, DC]: National Aeronautics and Space Administration, 1997.

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United States. National Aeronautics and Space Administration., ed. Multi-dimensional measurements of combustion species in flame tube and sector gas turbine combustors. [Washington, DC]: National Aeronautics and Space Administration, 1996.

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Multi-dimensional measurements of combustion species in flame tube and sector gas turbine combustors. [Washington, DC]: National Aeronautics and Space Administration, 1996.

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United States. National Aeronautics and Space Administration., ed. Multi-dimensional measurements of combustion species in flame tube and sector gas turbine combustors. [Washington, DC]: National Aeronautics and Space Administration, 1996.

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Conference papers on the topic "Gas-turbine flame analysis"

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Ohtsuka, Masaya, Shohei Yoshida, Shin’ichi Inage, and Nariyoshi Kobayashi. "Combustion Oscillation Analysis of Premixed Flames at Elevated Pressures." In ASME 1998 International Gas Turbine and Aeroengine Congress and Exhibition. American Society of Mechanical Engineers, 1998. http://dx.doi.org/10.1115/98-gt-581.

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A new analytical time lag flame model based on Bloxidge’s flame model was introduced for calculating combustion oscillation of premixed flame to take into account the distribution of heat release rate and flame speed which was calculated by analytical formulas dependent on pressure, temperature, fuel-to-air ratio and velocity. The transfer matrix technique using the new flame model was applied to the calculation of acoustic resonance. To verify the model, combustion oscillation experiments were performed for methane-air premixed flames stabilized by a swirl burner at elevated pressures between 0.6–0.9MPa. Fluctuating pressure had the maximum peak at the specific value of fτf. Here f is the frequency of resonance and τf is the passing time of premixed gas through flame length. The analysis could simulate the dependency of fuel-to-air ratio and static pressure for dynamic pressure local peak.
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Kumar, Arkadeep, Kamalika Chatterjee, Achintya Mukhopadhyay, and Swarnendu Sen. "Experimental Characterization of Premixed Flame in Gas Turbine Combustor With Spectroscopy and RGB Analysis." In ASME 2012 Gas Turbine India Conference. American Society of Mechanical Engineers, 2012. http://dx.doi.org/10.1115/gtindia2012-9604.

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Gas turbine combustion has been one of the principal sources for power generation and propulsion systems. Recent research thrust on flame monitoring for characterization of flame behavior has gained prominence for several reasons — notably for performance of combustor in aerospace propulsion and power plant applications, reduction in pollutant levels like NOx, and fire safety engineering, Lean air-fuel mixture leads to efficient combustion with lesser emissions, albeit with risk of Lean blow out (LBO). Flame monitoring is done to find out LBO point-which occurs by progressively varying the Air-fuel ratio or equivalence ratio. The current paper monitors the characteristics of lean premixed, swirl-stabilized, LPG fueled, dump combustor with the help of spectroscopy and high resolution camera images. Chemiluminescence is being used for determination of combustion characteristics. The spectroscopic peaks for chemical species like - OH* and CH* radicals and water vapor are found at varying parameters like air-fuel premixing and equivalence ratio. Blow off characteristics which occur in gas turbine combustor when going from rich to lean mixture are investigated. The comparison of the averaged red, green and blue (R, G, B) values has been done by graphical representation. The spectroscopic data are co-related with the RGB analysis results- and the location of spectroscopic peaks of intensities and their correspondence with electromagnetic spectrum in investigated. The behavior of peak intensities of Red, Green, Blue alongwith irradiation by chemical species – with the change in parameters like air flow rate, fuel flow rate or equivalence ratio and the extent of air-fuel premixing are investigated. Metrics for detecting the approach of impending LBO are proposed from the spectroscopic results.
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Krishna, C. Vamsi, and Santosh Hemchandra. "Reduced Order Modelling of Combustion Instability in a Backward Facing Step Combustor." In ASME 2013 Gas Turbine India Conference. American Society of Mechanical Engineers, 2013. http://dx.doi.org/10.1115/gtindia2013-3559.

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This paper develops a fully coupled time domain Reduced Order Modelling (ROM) approach to model unsteady combustion dynamics in a backward facing step combustor. The acoustic field equations are projected onto the canonical acoustic eigenmodes of the systems to obtain a coupled system of modal evolution equations. The heat release response of the flame is modelled using the G-equation approach. Vortical velocity fluctuations that arise due to shear layer rollup downstream of the step are modelled using a simplified 1D-advection equation whose phase speed is determined from a linear, local, temporal stability analysis of the shear layer, just downstream of the step. The hydrodynamic stability analysis reveals a abrupt change in the value of disturbance phase speed from unity for Re < Recrit to 0.5 for Re > Recrit, where Recrit for the present geometry was found to be ≈ 10425. The results for self-excited flame response show highly wrinkled flame shapes that are qualitatively similar to those seen in prior experiments of acoustically forced flames. The effect of constructive and destructive interference between the two contributions to flame surface wrinkling results in high amplitude wrinkles for the case when Kc → 1.
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De Rosa, Alexander J., Janith Samarasinghe, Stephen J. Peluso, Bryan D. Quay, and Domenic A. Santavicca. "Flame Area Fluctuation Measurements in Velocity-Forced Premixed Gas Turbine Flames." In ASME Turbo Expo 2015: Turbine Technical Conference and Exposition. American Society of Mechanical Engineers, 2015. http://dx.doi.org/10.1115/gt2015-42529.

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Fluctuations in the heat release rate that occur during unstable combustion in lean premixed gas turbine combustors can be attributed to velocity and equivalence ratio fluctuations. For a fully premixed flame, velocity fluctuations affect the heat release rate primarily by inducing changes in the flame area. In this paper, a technique to analyze changes in flame area using chemiluminescence-based flame images is presented. The technique decomposes the flame area into separate components which characterize the relative contributions of area fluctuations in the large scale structure and the small scale wrinkling of the flame. The fluctuation in the wrinkled area of the flame which forms the flame brush is seen to dominate its response in the majority of cases tested. Analysis of the flame area associated with the large scale structure of the flame resolves convective perturbations that move along the mean flame position. Results are presented that demonstrate the application of this technique to both single-nozzle and multi-nozzle flames.
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Ax, Holger, Ulrich Stopper, Wolfgang Meier, Manfred Aigner, and Felix Gu¨the. "Experimental Analysis of the Combustion Behavior of a Gas Turbine Burner by Laser Measurement Techniques." In ASME Turbo Expo 2009: Power for Land, Sea, and Air. ASMEDC, 2009. http://dx.doi.org/10.1115/gt2009-59171.

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Experimental results from optical and laser spectroscopic measurements on a scaled industrial gas turbine (GT) burner at elevated pressure are presented. Planar laser induced fluorescence on the OH radical and OH* chemiluminescence imaging were applied to natural gas/air flames for a qualitative analysis of the position and shape of the flame brush, the flame front and the stabilization mechanism. The results exhibit two different ways of flame stabilization, a conical more stable flame and a pulsating opened flame. For quantitative results, 1D-laser Raman scattering was applied to these flames and evaluated on an average and single shot basis in order to simultaneously determine the major species concentrations, the mixture fraction and the temperature. The mixing of fuel and air as well as the reaction progress could thus be spatially and temporally resolved, showing differently strong variations depending on the flame stabilization mode and the location in the flame.
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Rajagopal, Manikanda, Abdullah Karimi, and Razi Nalim. "Wave-Rotor Pressure-Gain Combustion Analysis for Power Generation and Gas Turbine Applications." In ASME 2012 Gas Turbine India Conference. American Society of Mechanical Engineers, 2012. http://dx.doi.org/10.1115/gtindia2012-9741.

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A wave-rotor pressure-gain combustor (WRPGC) ideally provides constant-volume combustion and enables a gas turbine engine to operate on the Humphrey-Atkinson cycle. It exploits pressure (both compression and expansion) waves and confined propagating combustion to achieve pressure rise inside the combustor. This study first presents thermodynamic cycle analysis to illustrate the improvements of a gas turbine engine possible with a wave rotor combustor. Thereafter, non-steady reacting simulations are used to examine features and characteristics of a combustor rig that reproduces key features of a WRPGC. In the thermodynamic analysis, performance parameters such as thermal efficiency and specific power are estimated for different operating conditions (compressor pressure ratio and turbine inlet temperature). The performance of the WRPGC is compared with the conventional unrecuperated and recuperated engines that operates on the Brayton cycle. Fuel consumption may be reduced substantially with WRPGC introduction, while concomitantly boosting power. Simulations have been performed of the ignition of propane by a hot gas jet and subsequent turbulent flame propagation and shock-flame interaction.
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Gorski, Jan, Wajid Ali Chishty, and Matthew Johnson. "Flame Response Analysis of Syngas." In ASME Turbo Expo 2014: Turbine Technical Conference and Exposition. American Society of Mechanical Engineers, 2014. http://dx.doi.org/10.1115/gt2014-25409.

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The motivation for the work comes from the requirement to assess the feasibility of using alternative fuels in lean-premixed land-based stationary gas turbine combustion systems. Lean-premixed systems are prone to combustion instability issues and the need is to determine how the use of alternative fuels would affect such instabilities. The paper presents the results of an acoustically-forced laminar flat flame study that was conducted to measure the influence of flow velocity oscillations on the response of syngas flames under various operating conditions and in comparison to natural gas flames. The results indicate that syngas concentration in a methane-syngas-air mixture significantly affects the flame response. On the other hand, the ratio of hydrogen-to-carbon monoxide in the syngas was found to have a negligible effect on the flame response for a fuel blend made up of 50% methane and 50% syngas. Flame liftoff distance and flame speed were found to be important parameters that govern the flame transfer function magnitude and resonant frequency for a thermally stabilized flat flame. The paper also presents insights into flame transfer function scaling based on a refined Strouhal definition.
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Hassan, Tarik, Sourav Sarkar, Achintya Mukhopadhyay, and Swarnendu Sen. "Characterization of Burner Stabilized Premixed and Non-Premixed Flame Using Digital Image Processing." In ASME 2019 Gas Turbine India Conference. American Society of Mechanical Engineers, 2019. http://dx.doi.org/10.1115/gtindia2019-2558.

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Abstract The present goal of combustion research is to enhance the burning efficiency resulting in minimal emission which is in fact, paves the way for a sustainable future. Researchers are investigating different parameters and factors associated with combustion to control the combustion process. Image processing is one of the most useful and safe tool for this job as it is nonintrusive and do not interfere with the combustion zone during experiment. Present work focuses on the digital image processing of the premixed and diffusion flame which has been utilized as a tool to characterize burner stabilized premixed and non-premixed Flame. The experiment is performed on a burner stabilized LPG-air flame. For premixed flame, several sets of experiments are done keeping the camera setting and image quality identical which resulted in an almost linearly increasing average RGB value with respect to equivalence ratio. Taking the relation of an experiment as standard, equivalence ratio is calculated for other experiments just by observing the average RGB value(R+G+B/3) of that image. It is found that almost in all cases the error values are lying between −10% to +10% of the actual value calculated from the flow rates of air and fuel. Diffusion flame is examined by passing fuel through the central channel of co-flow burner and air through the outer cylindrical channel. Air is used to stabilize the flame and for giving it a steady shape. Experiment is done keeping air flow constant while the fuel flow is varied and the image is captured. For diffusion flame, as the change in colour of flame is not much differentiable with the change in fuel, analysis is done to find the relation between fuel flow rate and flame area by counting the number of pixels. Finally, a direct relation of fuel amount and the image area is obtained.
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Gardiner, D. P., G. Pucher, W. D. Allan, and M. LaViolette. "Flame-Out Detection for Gas Turbine Engines Based Upon Thermocouple Signal Analysis." In ASME Turbo Expo 2006: Power for Land, Sea, and Air. ASMEDC, 2006. http://dx.doi.org/10.1115/gt2006-91080.

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This paper describes an experimental study to examine the potential of using Exhaust Gas Temperature (EGT) thermocouples for prompt flame-out detection in gas turbine engines. The approach taken involved accelerating the response of a shielded, slow response thermocouple using electronic processing of the signal. Thus, the abrupt drop in temperature characteristic of a flame-out could be detected within a much shorter time period than would be possible through a conventional thermocouple temperature measurement method. This was intended to provide a robust alternative to existing optical flame-out sensors which have fast response but can be susceptible to false flame-out indications due to window sooting. A production EGT thermocouple with online electronic processing was compared with a production optical flame sensor from a GE F-404 and a laboratory photodiode sensing system. The devices were tested in a full scale GE J-85 combustion chamber sector rig with optical access. The results showed that the thermocouple flame sensor had a response time to flame-outs of less than 100 ms. This was much faster than a conventional thermocouple, but still an order of magnitude longer than the optical flame sensor. However, whereas the optical flame sensor could yield ambiguous results about the presence of flame under some conditions, the thermocouple flame sensor provided a clear indication of flame-out events for all the conditions that were tested.
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Jung, Seung-chai, Siwon Yang, Shaun Kim, Ik Soo Kim, Chul-ju Ahn, Ju Hyeong Cho, Jisu Yoon, Youngbin Yoon, Samson Yoon, and Shiyang Ryu. "Development of Low Emission Gas Turbine Combustors." In ASME Turbo Expo 2015: Turbine Technical Conference and Exposition. American Society of Mechanical Engineers, 2015. http://dx.doi.org/10.1115/gt2015-42002.

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Abstract:
Due to increasing environmental concerns, clean technology has become a key feature in industrial gas turbines. Swirler design is directly associated with the combustion performance for its roles in fuel distribution and flame stability. In this study, the development process of three new conceptual swirlers from Samsung Techwin is presented. Each swirler has unique features to enhance fuel-to-air mixing; Swirler 1 uses tangential air-bypass, Swirler 2 minimizes pressure loss using impeller-like design, and Swirler 3 has combined flow characteristics of axial and radial swirlers. Using extensive computational fluid dynamics (CFD) analysis, lead time and cost in manufacturing the prototypes were significantly reduced. The numerical methods were verified with a lab-scale combustion test; particle image velocimetry (PIV) measurement of cold flow, direct flame images, and OH planar laser induced fluorescence (PLIF) images were compared with result of large-eddy simulation (LES), and they showed good agreement. After design optimization using CFD, full-scale combustion tests were performed for all three swirlers. Flame from each swirler was visualized using a cylindrical quartz liner; direct images and OH chemiluminescence images of flames were obtained. Flame stability and blow-off limit at various air load were examined by gradually lowering the equivalence ratio. NOx and CO concentration were measured at the exhaust. All three swirlers satisfied low NOx and CO levels at the design conditions. The performance maps bounded by the NOx and CO limits and blow-off limit were obtained for all swirlers. Further efforts to maximize the combustors performance will be made.
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