Relevant bibliographies by topics / Gas turbine combustion chambers

Academic literature on the topic 'Gas turbine combustion chambers'

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Published: 10 December 2022
Last updated: 28 January 2023

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Journal articles on the topic "Gas turbine combustion chambers"

1

Serbin, Sergey. "THERMO ACOUSTIC PROCESSES IN LOW EMISSION COMBUSTION CHAMBER OF GAS TURBINE ENGINE CAPACITY 25 MW." Science Journal Innovation Technologies Transfer, no. 2019-2 (May 5, 2019): 86–90. http://dx.doi.org/10.36381/iamsti.2.2019.86-90.

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The appliance of modern tools of the computational fluid dynamics for the investigation of the pulsation processes in the combustion chamber caused by the design features of flame tubes and aerodynamic interaction compressor, combustor and turbine is discussed. The aim of the research is to investigate and forecast the non-stationary processes in the gas turbine combustion chambers. The results of the numerical experiments which were carried out using three-dimensional mathematical models in gaseous fuels combustion chambers reflect sufficiently the physical and chemical processes of the unsteady combustion and can be recommended to optimize the geometrical and operational parameters of the low-emission combustion chamber. The appliance of such mathematical models are reasonable for the development of new samples of combustors which operate at the lean air-fuel mixture as well as for the modernization of the existing chambers with the aim to develop the constructive measures aimed at reducing the probability of the occurrence of the pulsation combustion modes. Keywords: gas turbine engine, combustor, turbulent combustion, pulsation combustion, numerical methods, mathematical simulation.
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Matyunin, O. O., S. K. Arkhipov, A. A. Shilova, N. L. Bachev, and R. V. Bulbovich. "Analysis of the combustion characteristics of hydrogen and hydrocarbon fuels based on the results of numerical simulation." Problems of the Regional Energetics, no. 3(55) (August 2022): 54–67. http://dx.doi.org/10.52254/1857-0070.2022.3-55.05.

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At present, an upward trend in the field of studying the processes of hydrogen combustion in the combustion chambers of the ground-based gas turbine power plants is obvious. The use of pure hydrogen as a fuel gas would solve the problem of environmental decarbonization. One of the emerging problems is to ensure the stable combustion of such fuels in combustion chambers of various applications. The information-analytical review of studies showed that there is a large number of theoretical and experimental results on the diffusion and homogeneous combustion of hydrogen and hydrogen-containing fuels in various burners and combustion chambers, which are not part of the existing gas turbine power plants. The purpose of this work is a comparative analysis of the gas-dynamic and emission characteristics of the combustion of the hydrogen-air and methane-air components based on the results of numerical simulation of a convertible combustion chamber of a 75 kW microgas turbine power plant. This goal is achieved by numerical simulation of the diffusion combustion of hydrogen and methane with air in a convertible combustion chamber. The most significant result of the work is obtaining the isosurface of the flame, which made it possible to obtain the conditions for stable combustion in the form of the Damköhler criterion and the ratio of the midsection velocity to the velocity of turbulent combustion. The significance of the results obtained lies in the further development of the methodology for the conversion of megawatt-class gas turbine plants to hydrogen and hydrogencontaining fuels.
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Kru¨ger, U., J. Hu¨ren, S. Hoffmann, W. Krebs, P. Flohr, and D. Bohn. "Prediction and Measurement of Thermoacoustic Improvements in Gas Turbines With Annular Combustion Systems." Journal of Engineering for Gas Turbines and Power 123, no. 3 (October 1, 2000): 557–66. http://dx.doi.org/10.1115/1.1374437.

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Environmental compatibility requires low emission burners for gas turbine power plants. In the past, significant progress has been made developing low NOx and CO burners by introducing lean premixed techniques in combination with annular combustion chambers. Unfortunately, these burners often have a more pronounced tendency to produce combustion-driven oscillations than conventional burner designs. The oscillations may be excited to such an extent that the risk of engine failure occurs. For this reason, the prediction of these thermoacoustic instabilities in the design phase of an engine becomes more and more important. A method based on linear acoustic four-pole elements has been developed to predict instabilities of the ring combustor of the 3A-series gas turbines. The complex network includes the whole combustion system starting from both compressor outlet and fuel supply system and ending at the turbine inlet. The flame frequency response was determined by a transient numerical simulation (step-function approach). Based on this method, possible improvements for the gas turbine are evaluated in this paper. First, the burner impedance is predicted theoretically and compared with results from measurements on a test rig for validation of the prediction approach. Next, the burner impedance in a gas turbine combustion system is analyzed and improved thermoacoustically. Stability analyses for the gas turbine combustion system show the positive impact of this improvement. Second, the interaction of the acoustic parts of the gas turbine system has been detuned systematically in circumferential direction of the annular combustion chamber in order to find a more stable configuration. Stability analyses show the positive effect of this measure as well. The results predicted are compared with measurements from engine operation. The comparisons of prediction and measurements show the applicability of the prediction method in order to evaluate the thermoacoustic stability of the combustor as well as to define possible countermeasures.
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Mevissen, Frank, and Michele Meo. "A Review of NDT/Structural Health Monitoring Techniques for Hot Gas Components in Gas Turbines." Sensors 19, no. 3 (February 9, 2019): 711. http://dx.doi.org/10.3390/s19030711.

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The need for non-destructive testing/structural health monitoring (SHM) is becoming increasingly important for gas turbine manufacturers. Incipient cracks have to be detected before catastrophic events occur. With respect to condition-based maintenance, the complex and expensive parts should be used as long as their performance or integrity is not compromised. In this study, the main failure modes of turbines are reported. In particular, we focus on the turbine blades, turbine vanes and the transition ducts of the combustion chambers. The existing monitoring techniques for these components, with their own particular advantages and disadvantages, are summarised in this review. In addition to the vibrational approach, tip timing technology is the most used technique for blade monitoring. Several sensor types are appropriate for the extreme conditions in a gas turbine, but besides tip timing, other technologies are also very promising for future NDT/SHM applications. For static parts, like turbine vanes and the transition ducts of the combustion chambers, different monitoring possibilities are identified and discussed.
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Mrzljak, Vedran, Nikola Anđelić, Ivan Lorencin, and Zlatan Car. "Analysis of Gas Turbine Operation before and after Major Maintenance." Journal of Maritime & Transportation Science 57, no. 1 (December 2019): 57–70. http://dx.doi.org/10.18048/2019.57.04.

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This paper presents an analysis of the gas turbine real process (with all losses included) before and after a major maintenance. The analysis of both gas turbine operating regimes is based on data measured during its exploitation. Contrary to authors’ expectations, the major maintenance process did not result either in any decrease in losses or increase in efficiencies for the majority of the gas turbine components. However, the major maintenance influenced positively the gas turbine combustion chambers (reduction in losses and increase in the combustion chambers efficiency). After the major maintenance, the overall process efficiency decreased from 43.796% to 41.319% due to a significant decrease in the air mass flow rate and to an increase in the fuel mass flow rate in combustion chambers. A decrease in the gas turbine produced cumulative and useful power after a major maintenance also increased the specific fuel consumption.
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Brandauer, M., A. Schulz, and S. Wittig. "Mechanisms of Coke Formation in Gas Turbine Combustion Chambers." Journal of Engineering for Gas Turbines and Power 118, no. 2 (April 1, 1996): 265–70. http://dx.doi.org/10.1115/1.2816587.

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New gas turbine combustor designs are developed to reduce pollutant and NOx emissions. In these new combustors, the formation of carbonaceous deposits, especially in prevaporizers, affects the reliability and effectiveness of operation. To avoid deposits, a detailed knowledge of the origins and mechanisms of formation is required. To obtain a deeper insight, the phenomena were studied systematically. The deposits under consideration show differing characteristics suggesting more than one formation mechanism in the combustor. Consequently, the primary goal was to identify the formation mechanisms and, subsequently, to simulate the mechanisms under well-defined conditions in bench tests for determining the relevant parameters of deposit build-up. The mechanisms of formation were identified based on the properties of the deposits in the combustion chamber. In order to characterize the deposits, physical and chemical analysis techniques were utilized. In summary, tests and numerical predictions identified two major paths of formation: a deposit build-up resulting from flame products such as soot or coked droplets and a deposit build-up resulting from liquid fuel impinging the wall accompanied with chemical reactions at the wall. The deposits caused by fuel droplet impingement were intensively studied in bench tests. In analyzing the processes, the influence of wall temperature, fuel composition, and the oxygen content in the environment is shown in detail. In addition, the importance of thermal instabilities of the fuel, previously studied under fuel supply system conditions, is demonstrated for a deposit formation inside a combustion chamber.
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Iurashev, Dmytro, Giovanni Campa, Vyacheslav V. Anisimov, and Ezio Cosatto. "Two-step approach for pressure oscillations prediction in gas turbine combustion chambers." International Journal of Spray and Combustion Dynamics 9, no. 4 (May 30, 2017): 424–37. http://dx.doi.org/10.1177/1756827717711016.

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Currently, gas turbine manufacturers frequently face the problem of strong acoustic combustion-driven oscillations inside combustion chambers. These combustion instabilities can cause extensive wear and sometimes even catastrophic damage of combustion hardware. This requires prevention of combustion instabilities, which, in turn, requires reliable and fast predictive tools. We have developed a two-step method to find a set of operating parameters under which gas turbines can be operated without going into self-excited pressure oscillations. As the first step, an unsteady Reynolds-averaged Navier–Stokes simulation with the flame speed closure model implemented in the OpenFOAM® environment is performed to obtain the flame transfer function of the combustion set-up. As the second step time-domain simulations employing low-order network model implemented in Simulink® are executed. In this work, we apply the proposed method to the Beschaufelter RingSpalt test rig developed at the Technische Universität München. The sensitivity of thermoacoustic stability to the length of a combustion chamber, flame position, gain and phase of flame transfer function and outlet reflection coefficient are studied.
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Perevoschikov, S. I. "PROCEDURE OF PARAMETRIC DIAGNOSTICS OF GAS PUMPING UNITSWITH TURBINE DRIVE." Oil and Gas Studies, no. 5 (November 1, 2016): 101–8. http://dx.doi.org/10.31660/0445-0108-2016-5-101-108.

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The article describes the procedure of parametric diagnostics of gas pumping units with a turbine drive which enables to detect the unit state on the minimum information base with determination of the diagnostic conclusions probability. A two-level diagnostics is considered, namely by the units basic components (their injectors and gas turbine units, GTU) and by the GTU components (axial compressors, turbines and combustion chambers).
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Noiray, Nicolas, and Bruno Schuermans. "On the dynamic nature of azimuthal thermoacoustic modes in annular gas turbine combustion chambers." Proceedings of the Royal Society A: Mathematical, Physical and Engineering Sciences 469, no. 2151 (March 8, 2013): 20120535. http://dx.doi.org/10.1098/rspa.2012.0535.

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This paper deals with the dynamics of standing and rotating azimuthal thermoacoustic modes in annular combustion chambers. Simultaneous acoustic measurements have been made at multiple circumferential positions in an annular gas turbine combustion chamber. A detailed statistical analysis of the spatial Fourier amplitudes extracted from these data reveals that the acoustic modes are continuously switching between standing, clockwise and counter-clockwise travelling waves. A theoretical framework from which the modal dynamics can be explained is proposed and supported by real gas turbine data. The stochastic differential equations that govern these systems have been derived and used as a basis for system identification of the measured engine data. The model describes the probabilities of the two azimuthal wave components as a function of the random source intensity, the asymmetry in the system and the strength of the thermoacoustic interaction. The solution of the simplified system is in good agreement with experimental observations on a gas turbine combustion chamber.
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Iurashev, Dmytro, Giovanni Campa, Vyacheslav V. Anisimov, Ezio Cosatto, Luca Rofi, and Edoardo Bertolotto. "Application of a three-step approach for prediction of combustion instabilities in industrial gas turbine burners." Journal of the Global Power and Propulsion Society 1 (July 21, 2017): JCW78T. http://dx.doi.org/10.22261/jcw78t.

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Abstract Recently, because of environmental regulations, gas turbine manufacturers are restricted to produce machines that work in the lean combustion regime. Gas turbines operating in this regime are prone to combustion-driven acoustic oscillations referred as combustion instabilities. These oscillations could have such high amplitude that they can damage gas turbine hardware. In this study, the three-step approach for combustion instabilities prediction is applied to an industrial test rig. As the first step, the flame transfer function (FTF) of the burner is obtained performing unsteady computational fluid dynamics (CFD) simulations. As the second step, the obtained FTF is approximated with an analytical time-lag-distributed model. The third step is the time-domain simulations using a network model. The obtained results are compared against the experimental data. The obtained results show a good agreement with the experimental ones and the developed approach is able to predict thermoacoustic instabilities in gas turbines combustion chambers.
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Dissertations / Theses on the topic "Gas turbine combustion chambers"

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Kister, Guillaume. "Ceramic-matrix composites for gas turbine applications." Thesis, University of Bath, 1999. http://ethos.bl.uk/OrderDetails.do?uin=uk.bl.ethos.299850.

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Cavaliere, Davide Egidio. "Blow-off in gas turbine combustors." Thesis, University of Cambridge, 2014. https://www.repository.cam.ac.uk/handle/1810/265575.

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This thesis describes an experimental investigation of the flame structure close to the extinction and the blow-off events of non-premixed and spray flames stabilized on an axisymmetric bluff body in a confined swirl configuration. The comparison of flames of different canonical types in the same basic aerodynamic field allows insights on the relative blow-off behaviour. The first part of the thesis describes several velocity measurements in non-reacting and reacting flows. The main usefulness of this data is to provide the aerodynamic flow pattern and some discussion on the velocity field and the related recirculation zones. The velocity and turbulence information obtained are particularly useful for providing data, which is crucial for validation of computational models. The second part describes an experimental investigation of non-premixed stable flames very close to the blow-off condition. The measurements included visualisation of the blow-off transient with 5 kHz OH* chemiluminescence, which allowed a quantification of the average duration of the blow-off transient. OH-PLIF images at 5 kHz for flames far from and close to extinction showed that the non-premixed flame intermittently lifts-off the bluff body, with increasing probability as the fuel velocity increases. The flame sheet shows evidence of localised extinctions, which are more pronounced as approaching blow-off. The measurements include blow-off limits and their attempted correlation. It was found that a correlation based on a Damkohler number does a reasonable job at collapsing the dataset. The final part examines the blow-off behaviour of swirling spray flames for two different fuels: n-heptane and n-decane. The measurements include blow-off limits and their att~mpted correlation, visualisation of the blow-off transient with 5 kHz OH* chemiluminescence, and the quantification of the average duration of the blow-off transient. It was found that the average duration of the blow-off event is in order of the tens of ms for both spray flames (10-16 ms). The blow-off event is therefore a relatively slow process for the spray ~ames using n-heptane and decane fuels. This suggests that control measures, such as fast fuel injection, coupled with appropriate detection, such as with chemiluminescence monitoring, may have a reasonable chance of success in keeping the flame alight very close to the blow-off limit. These results, together with those obtained for the non-premixed gaseous case form a wide body of experimental data available for the validation of turbulent flame models. The quantification of some properties during the blow-off transient can assist studies of extinction based on large-eddy simulation that have a promise of capturing combustion transients.
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Bainbridge, William David Quillen. "The numerical similation of oscillations in gas turbine combustion chambers." Thesis, University of Cambridge, 2014. http://ethos.bl.uk/OrderDetails.do?uin=uk.bl.ethos.648428.

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Fortunato, Valentina. "Development and testing of combustion chambers for residential micro gas turbine applications." Doctoral thesis, Universite Libre de Bruxelles, 2017. http://hdl.handle.net/2013/ULB-DIPOT:oai:dipot.ulb.ac.be:2013/256708.

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Nowadays, in the field of energy production, particular attention must be paid to improving efficiency, reducing pollutants and fuel flexibility. To reach those goals, cogenerative systems represent an appealing solution. One of the most promising cogenerative systems available nowadays is the micro turbine, which provides reasonable electrical efficiency of about 30%, multi-fuel capability, low emission levels and heat recovery potential, and need minimum maintenance. Among the several options, micro gas turbines (mGT) are particularly interesting. Beside theuse of natural gas, other fuels like landfill gas, ethanol, industrial waste off-gases and other bio-based gases can be used. Moreover, it is possible to further improve the efficiencies and reduce the emissions for mGTs by paying particular attention at the design of the combustion chamber. To this goal, flameless combustion could be an interesting solution. Flameless combustion is able to provide high combustion efficiency with low NOx and soot emissions. The increasing interest in flameless combustion is motivated by its large fuel flexibility, representing a promising technology for low-calorific value fuels, high-calorific industrial wastes as well as in presence of hydrogen. Moreover, flameless combustion is very stableand noiseless, so it is suited for gas turbine applications where conventional operations may lead to significant thermo-acoustic instabilities (“humming”) and stresses. Flameless combustion needs the reactants to be preheated above their self-ignition temperature and enough inert combustion products to be entrained in the reaction region, in order to dilute the flame. As a result, the temperature field is more uniform than in traditional combustion systems, and it does not show high temperature peaks. Hence, NOx formation is suppressed as well as soot formation,due to the lean conditions, low temperatures and the large CO2 concentration in the exhausts.mGTs operating in flameless combustion regime represent a promising technology for the combined production of heat and power with increased efficiency, reduced pollutants emission and high fuel flexibility. The objective of the present Thesis is the design of a combustion chamber for amGT for residential applications. The design is performed employing CFD-tools. Thus, it is necessary to develop a reliable numerical model to use in the design process. Therefore, the first step of the Thesis consists in a series of validation studies, with the goal of selecting the most appropriate and reliable models to describe flameless combustion. The validation will be carried on three differenttest cases, which have different nominal powers and employ different gaseous fuels. The second part of the Thesis focuses on the design and optimization of the combustion chamber. Finally, the third part shows the experimental investigation of the aforementioned chamber.The study of those three cases shows that, to correctly predict the behavior of those systems, it is necessary to take into account both mixing and chemical kinetics. The best results have been obtained with the Eddy Dissipation Concept model, coupled with detailed kinetic schemes. As far as the NOx emissions are concerned, it is fundamental to include all the formation routes, i.e. thermal, prompt, via N2O and NNH route, to estimate properly the NOx production in flameless conditions.The aforementioned models have been used for the design and optimization of a combustion chamber for a mGT operating in flameless combustion regime. Both the design and the optimization have been carried out by means of CFD simulations and both are goal-oriented, meaning that they are carried out with the purpose of improving one or more performance indicators of the chamber, such as pollutants emissions, efficiency or pressure losses. The configuration that satisfies the criteria on the performance indicators has been built and investigated experimentally. The combustion chamber is stable and performs well in terms of emissions for a wide range of air inlet temperature and air-fuel equivalence ratio, lambda, values. Except for the condition closer to the stoichiometric one, both CO and NOx emissions are extremely low for all !and air inlet temperatures. Thechamber performs the best at its nominal operating condition, i.e. lambda = 3.5 and air inlet temperature 730 °C, In this case CO is 0 ppm and NOx is 5.6 ppm. The numerical model employed to describe the combustor performs quite well, except for the CO prediction, for all the conditions investigated. The final step of the present work is the application of a different kind of fuel, namely biogas. First the feasibility of such application has been evaluated using CFD calculations, and then the experimental evidence has been discussed. Due to a calibration error on the gas flow meter, it has not been possible to investigate the conditions of the design point (lambda = 3.5). Three other conditions have been examined,characterized by lower values of !closer to the stoichiometric conditions. Despite the relatively high values of NOx emissions due to the lower air excess and to the consequently higher temperatures, the combustion chamber has proven to be fuel flexible. Both ignition and stable combustion can be achieved also when biogas is burnt. Numerical simulations have also been performed; the results are in good agreement with the experimental evidence.
Doctorat en Sciences de l'ingénieur et technologie
info:eu-repo/semantics/nonPublished
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Ku, Shiuh-Huei. "An investigation of the gas fired pulsating combustor." Diss., Georgia Institute of Technology, 1988. http://hdl.handle.net/1853/13062.

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Farrell, Brian Henry. "An experimental and theoretical investigation into simple, low cost combustion chambers for small gas turbines." Thesis, Queen's University Belfast, 1989. http://ethos.bl.uk/OrderDetails.do?uin=uk.bl.ethos.335334.

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Neumeier, Yedidia. "Frequency domain analysis of a gas fired mechanically valved pulse combustor." Diss., Georgia Institute of Technology, 1993. http://hdl.handle.net/1853/13354.

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Robinson, Alexander. "Development and testing of hydrogen fuelled combustion chambers for the possible use in an ultra micro gas turbine." Doctoral thesis, Universite Libre de Bruxelles, 2012. http://hdl.handle.net/2013/ULB-DIPOT:oai:dipot.ulb.ac.be:2013/209706.

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The growing need of mobile power sources with high energy density and the robustness to operate also in the harshest environmental surroundings lead to the idea of downscaling gas turbines to ì-scale. Classified as PowerMEMS devices, a couple of design attempts have emerged in the last decade. One of these attempts was the Belgian “PowerMEMS” design started back in 2003 and aiming towards a ì-scale gas turbine rated at 1 kW of electrical power output.

This PhD thesis presents the scientific evaluation and development history of different combustion chamber designs based upon the “PowerMEMS” design parameters. With hydrogen as chosen fuel, the non-premixed diffusive “micromix” concept was selected as combustion principle. Originally designed for full scale gas turbine applications in two different variants, consequently the microcombustor development had to start with the downscaling of these two principles towards ì-scale. Both principles have the advantage to be inherently safe against flashback, due to the non-premixed concept, which is an important issue even in this small scale application when burning hydrogen. By means of water analogy and CFD simulations the hydrogen injection system and the chamber geometry could be validated and optimized. Besides the specific design topics that emerged during the downscaling process of the chosen combustion concepts, the general difficulties of microcombustor design like e.g. high power density, low Reynolds numbers, short residence time, and manufacturing restrictions had to be tackled as well.

As full scale experimental test campaigns are still mandatory in the field of combustion research, extensive experimental testing of the different prototypes was performed. All test campaigns were conducted with a newly designed test rig in a combustion lab modified for microcombustion investigations, allowing testing of miniaturized combustors according to full engine requirements with regard to mass flow, inlet temperature, and chamber pressure. The main results regarding efficiency, equivalence ratio, and combustion temperature were obtained by evaluating the measured exhaust gas composition. Together with the performed ignition and extinction trials, the evaluation and analysis of the obtained test results leads to a full characterization of each tested prototype and delivered vital information about the possible operating regime in a later UMGT application. In addition to the stability and efficiency characteristics, another critical parameter in combustor research, the NOx emissions, was investigated and analyzed for the different combustor prototypes.

As an advancement of the initial downscaled micromix prototypes, the following microcombustor prototype was not only a combustion demonstrator any more, but already aimed for easy module integration into the real UMGT. With a further optimized combustion efficiency, it also featured an innovative recuperative cooling of the chamber walls and thus allowing an cost effective all stainless steel design.

Finally, a statement about the pros and cons of the different micromix combustion concepts and their correspondent combustor designs towards a possible ì-scale application could be given.
Doctorat en Sciences de l'ingénieur
info:eu-repo/semantics/nonPublished

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Mohanraj, Rajendran. "Modeling of combustion instabilities and their active control in a gas fueled combustor." Diss., Georgia Institute of Technology, 1998. http://hdl.handle.net/1853/12089.

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Lieuwen, Tim C. "Investigation of combustion instability mechanisms in premixed gas turbines." Diss., Georgia Institute of Technology, 1999. http://hdl.handle.net/1853/20300.

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Books on the topic "Gas turbine combustion chambers"

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Shyy, W. A numerical study of flow in gas-turbine combustor. New York: AIAA, 1987.

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North Atlantic Treaty Organization. Advisory Group for Aerospace Research and Development. Advanced technology for aero gas turbine components. Neuilly sur Seine, France: AGARD, 1987.

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1969-, Xu Quanhong, and Liu Gao'en 1939-, eds. Ran qi lun ji ran shao shi: Cas turbine combustor. Beijing Shi: Guo fang gong ye chu ban she, 2008.

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Fuller, E. J. Integrated CFD modeling of gas turbine combustors. Washington, D. C: AIAA, 1993.

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Melconian, Jerry O. Introducing the VRT gas turbine combustor. [Washington, D.C.]: NASA, 1990.

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Bose, S. Materials for advanced turbine engines (MATE) project 3 design, fabrication and evaluation of an oxide dispersion strengthened sheet alloy combustor liner. [Washington, DC: National Aeronautics and Space Administration, 1990.

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Holdeman, J. D. A numerical study of the effects of curvature and convergence on dilution jet mixing. [Washington, D.C.]: National Aeronautics and Space Administration, 1987.

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Veres, Joseph P. Overview of high-fidelity modeling activities in the numerical propulsion system simulations (NPSS) project. [Cleveland, Ohio]: National Aeronautics and Space Administration, Glenn Research Center, 2002.

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Stewart, William E. Design guide: Combustion turbine inlet air cooling systems. Atlanta, Ga: American Society of Heating, Refrigerating and Air-Conditioning Engineers, 1999.

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Cawley, James D. Phenomenological study of the behavior of some silica formers in a high velocity jet fuel burner. [Cleveland, Ohio: National Aeronautics and Space Administration, Lewis Research Center, 1985.

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Book chapters on the topic "Gas turbine combustion chambers"

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Schobeiri, Meinhard T. "Modeling of Recuperators, Combustion Chambers, Afterburners." In Gas Turbine Design, Components and System Design Integration, 353–68. Cham: Springer International Publishing, 2017. http://dx.doi.org/10.1007/978-3-319-58378-5_14.

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Schobeiri, Meinhard T. "Modeling of Recuperators, Combustion Chambers, Afterburners." In Gas Turbine Design, Components and System Design Integration, 355–70. Cham: Springer International Publishing, 2019. http://dx.doi.org/10.1007/978-3-030-23973-2_14.

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Lebiedz, Dirk, and Jochen Siehr. "Simplified Reaction Models for Combustion in Gas Turbine Combustion Chambers." In Flow and Combustion in Advanced Gas Turbine Combustors, 161–82. Dordrecht: Springer Netherlands, 2012. http://dx.doi.org/10.1007/978-94-007-5320-4_5.

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Kneissl, S., D. C. Sternel, M. Schäfer, P. Pantangi, A. Sadiki, and J. Janicka. "Integral Model for Simulating Gas Turbine Combustion Chambers." In Flow and Combustion in Advanced Gas Turbine Combustors, 325–47. Dordrecht: Springer Netherlands, 2012. http://dx.doi.org/10.1007/978-94-007-5320-4_11.

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Marquetand, J., M. Fischer, I. Naydenova, and U. Riedel. "A Simplified Model for Soot Formation in Gas Turbine Combustion Chambers." In Flow and Combustion in Advanced Gas Turbine Combustors, 205–33. Dordrecht: Springer Netherlands, 2012. http://dx.doi.org/10.1007/978-94-007-5320-4_7.

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Ulbrich, S., and R. Roth. "Efficient Numerical Multilevel Methods for the Optimization of Gas Turbine Combustion Chambers." In Flow and Combustion in Advanced Gas Turbine Combustors, 379–411. Dordrecht: Springer Netherlands, 2012. http://dx.doi.org/10.1007/978-94-007-5320-4_13.

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Duwig, Christophe, and Laszlo Fuchs. "Large-Eddy Simulation of a Gas Turbine Combustion Chamber." In Direct and Large-Eddy Simulation V, 343–50. Dordrecht: Springer Netherlands, 2004. http://dx.doi.org/10.1007/978-1-4020-2313-2_37.

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Nakajima, T., and R. Matsumoto. "Velocity and Turbulence Measurements in Model Gas-Turbine Combustion Chambers and Comparison With A Model Calculation." In Laser Diagnostics and Modeling of Combustion, 55–62. Berlin, Heidelberg: Springer Berlin Heidelberg, 1987. http://dx.doi.org/10.1007/978-3-642-45635-0_7.

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Dev, Nikhil, Samsher, and S. S. Kachhwaha. "Simulation of Gas Turbine Combustion Chamber for CO2 Emission Minimization." In Advances in Intelligent and Soft Computing, 247–58. New Delhi: Springer India, 2012. http://dx.doi.org/10.1007/978-81-322-0491-6_24.

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Knoche, Ralf, Erich Werth, Markus Weth, Jesus Gómez García, Christian Wilhelmi, and Miklós Gerendás. "Design and Development Approach for Gas Turbine Combustion Chambers Made of Oxide Ceramic Matrix Composites." In Mechanical Properties and Performance of Engineering Ceramics and Composites VI, 77–87. Hoboken, NJ, USA: John Wiley & Sons, Inc., 2011. http://dx.doi.org/10.1002/9781118095355.ch7.

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Conference papers on the topic "Gas turbine combustion chambers"

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Tamaru, T., K. Shimodaira, Y. Kurosawa, and T. Kuyama. "Combustion Instability of a Gas Turbine Combustor up to 50-Atmosphere Condition." In ASME 1986 International Gas Turbine Conference and Exhibit. American Society of Mechanical Engineers, 1986. http://dx.doi.org/10.1115/86-gt-175.

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Combustion instabilities or blow-off phenomena at high pressure conditions were investigated on practical can-type combustion chambers. An air loading parameter, ma/VP2 at constant inlet temperature, was used to evaluate the allowable air flow rate in the combustion chamber. It was found that the pressure dependency of the parameter was not adequate for the high pressure conditions. It is revealed that the blow-off velocity in the flame holding region is related to the maximum laminar burning velocity corresponding to the pressure and temperature and that the velocity in the primary zone must be a very small value at high pressure condition.
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Klein, Sikke A., and Jim B. W. Kok. "Acoustic Instabilities in Syngas Fired Combustion Chambers." In ASME 1999 International Gas Turbine and Aeroengine Congress and Exhibition. American Society of Mechanical Engineers, 1999. http://dx.doi.org/10.1115/99-gt-355.

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Gas turbines fired on syngas may show thermo-acoustic combustion instabilities. The theory on these instabilities is well developed. From this theory it can be shown that the acoustic system of a combustion installation can be described as a control loop with a set of transfer functions. The transfer function of the flame plays a decisive role in the occurrence of combustion instabilities. It is however very difficult to predict this flame transfer function analytically. In this paper a numerical method will be presented to calculate the flame transfer function from time-dependent combustion calculations. Also an experimental method will be discussed to determine this flame transfer function. Experiments have been performed in a 25 kW atmospheric test rig. Also calculations have been done for this situation. The agreement between the measurements and CFD calculations is good, especially for the phase at higher frequencies. This opens the way to apply CFD-modeling for acoustics in a real gas turbine situation.
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Brandauer, M., A. Schulz, and S. Wittig. "Mechanisms of Coke Formation in Gas Turbine Combustion Chambers." In ASME 1995 International Gas Turbine and Aeroengine Congress and Exposition. American Society of Mechanical Engineers, 1995. http://dx.doi.org/10.1115/95-gt-049.

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New gas turbine combustor designs are developed to reduce pollutant and NOx-emissions. In these new combustors, the formation of carbonaceous deposits, especially in prevaporizers, affects the reliablility and effectiveness of operation. To avoid deposits, a detailed knowledge of the origins and mechanisms of formation is required. To obtain a deeper insight, the phenomena were studied systematically. The deposits under consideration show differing characteristics suggesting more than one formation mechanism in the combustor. Consequently, the primary goal was to identify the formation mechanisms and, subsequently, to simulate the mechanisms under well-defined conditions in bench tests for determining the relevant parameters of deposit build-up. The mechanisms of formation were identified based on the properties of the deposits in the combustion chamber. In order to characterize the deposits, physical and chemical analysis techniques were utilized. In summary, tests and numerical predictions identified two major paths of formation: a deposit build-up resulting from flame products such as soot or coked droplets and a deposit build-up resulting from liquid fuel impinging the wall accompanied with chemical reactions at the wall. The deposits caused by fuel droplet impingement were intensively studied in bench tests. In analyzing the processes, the influence of wall temperature, fuel composition, and the oxygen content in the environment is shown in detail. In addition, the importance of thermal instabilities of the fuel, previously studied under fuel supply system conditions, is demonstrated for a deposit formation inside a combustion chamber.
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Gherman, Bogdan, Robert-Zoltan Szasz, and Laszlo Fuchs. "LES of Swirling Flows in Gas Turbine Combustion Chambers." In ASME Turbo Expo 2004: Power for Land, Sea, and Air. ASMEDC, 2004. http://dx.doi.org/10.1115/gt2004-53711.

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The flow and mixing in a swirl-stabilized gas-turbine burner is studied by Large Eddy Simulations (LES). Each swirler has a different mass flux and swirl angle. The interaction between neighbouring jets is studied, co-rotating and counter rotating jets are considered. Another issue of importance is related to the jet inlet conditions (e.g. axial distribution and levels of turbulence). In addition to the flow field (using LES) we present results related to fuel/air mixing under different conditions. We show that the LES results can resolve several issues related to the burner that cannot be accounted for by the standard RANS computations.
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Sakurai, Takashi, and Shunsuke Nakamura. "Performance and Operating Characteristics of Micro Gas Turbine Driven by Pulse, Pressure Gain Combustor." In ASME Turbo Expo 2020: Turbomachinery Technical Conference and Exposition. American Society of Mechanical Engineers, 2020. http://dx.doi.org/10.1115/gt2020-15000.

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Abstract This paper presents the experimental results of a micro gas turbine driven by pulse, pressure gain combustor. The aim of this study is to demonstrate the improvement of the engine performance by applying the pressure gain combustion. The micro gas turbine is composed of a combustor having two combustion chambers and an automotive turbocharger which is used as a compressor and a turbine. The outlets of two combustion chambers are joined by a confluence part to connect with the turbine. By changing the combustion methods of each combustion chamber, the gas turbine was operated in three modes; normal combustion mode, pulse combustion augmented mode, and fully pulse combustion mode. In the normal combustion mode, two combustion chambers were operated under continuous, constant-pressure combustion. In the pulse combustion augmented mode, one combustion chamber was operated under continuous, constant-pressure combustion and the other was operated under pulse combustion. In the fully pulse combustion mode, two combustion chambers were operated under pulse combustion. The pulse combustion applied in this study was the forced-ignition type, active pulse combustion. Although the pressure increase was attained by the pulse combustion comparing with the normal combustion, the mass-averaged pressure in the combustor showed that the net pressure gain in the combustor was not attained. The engine performance such as thermal efficiency and work and operating characteristics of gas turbine were investigated for two operation modes. In the pulse combustion augmented mode, the gas turbine could successfully sustain its operation as well as normal operation mode. The increase in the combustor pressure affected the air mass flow rate and the compressor performance, resulted in the decrease of performance comparing with the normal combustion mode.
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Bauermeister, Kurt J., Bernhard Schetter, and Klaus D. Mohr. "A 9.25 MW Industrial Gas Turbine With Extreme Low Dry NOx and CO Emissions." In ASME 1993 International Gas Turbine and Aeroengine Congress and Exposition. American Society of Mechanical Engineers, 1993. http://dx.doi.org/10.1115/93-gt-307.

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In cooperation between Siemens and MAN GHH an industrial gas turbine with an ISO rating of 9.2 5 MW was equipped with a dry low NOx combustion system. Using the hybrid burners of Siemens gas turbines, a new combustion chamber was developed for the gas turbine THM 1304 of MAN GHH. This gas turbine has two V-like arranged combustion chambers, which allow a redesign of the combustion chamber, without changing the remaining parts of the gas turbine and its casing. So it is possible as well, to fit present machines with new combustion chambers. The combustion chambers contain flame tubes of Siemens technology with ceramic tiles and the well proved hybrid burners. After calculation and design the air flow was examined in an isothermal flow model. Finally two prototypes of the combustion chamber mounted on a THM 1304 gas turbine were tested at the MAN GHH gas turbine test bed. Success came very quickly and the test runs are finished now. So for the first time the transfer of the well-known low emission values of the Siemens large scale gas turbines succeeded to an industrial gas turbine of the 10 MW class.
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Medina, Pablo, Doris Saez, and Roberto Roman. "On Line Fault Detection and Isolation in Gas Turbine Combustion Chambers." In ASME Turbo Expo 2008: Power for Land, Sea, and Air. ASMEDC, 2008. http://dx.doi.org/10.1115/gt2008-51316.

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This work presents the development of a new model for the exhaust gas temperature based on both basis function expansion and the Brayton cycle. This model is a function of the power generated, ambient temperature, compression rate, and the temperature of each combustion chamber. This last temperature is unknown, but could be estimated. The model basis functions also include the spatial distribution of the combustion chamber and exhaust gases swirl angle surface. Thus, based on the gas path in the turbine, each base function of the model is related to a particular combustion chamber. This is the main assumption that allows solving the fault detection and isolation problem in gas turbines at the level of combustion chambers. As a result of the model identification at every instant, there is a group of coefficients, which are associated to each combustion chamber. From these coefficients, it is possible to generate signals that can be analyzed with statistical techniques and also with wavelets to detect abrupt changes in its behavior.
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Sakurai, Takashi, Takehiro Sekiguchi, and Sora Inoue. "Evaluation of Pressure Gain and Turbine Inlet Conditions in a Pulse Combustion Gas Turbine." In ASME Turbo Expo 2022: Turbomachinery Technical Conference and Exposition. American Society of Mechanical Engineers, 2022. http://dx.doi.org/10.1115/gt2022-83528.

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Abstract This study investigates the pressure gain and its improvement on the gas turbine performance. The combustor is comprised from two combustion chambers. One chamber A conducts pulse combustion and the other chamber B conducts continuous, constant-pressure combustion. The burned gases of each chamber are mixed and enter the turbine. The detail time variation of chamber pressure as well as turbine inlet and compressor outlet under the pulse combustion mode were experimentally investigated. The pulse combustion in the chamber A generated the pressure wave that propagated not only downstream to the turbine inlet but also chamber upstream. This pressure wave stagnated the gas flow from the compressor in the chamber A. The gas flow velocities at the chamber inlet and outlet of chamber A were measured. The results showed the large velocity variation in one cycle under the pulse combustion mode. Based on the velocity, the cycle-averaged pressures in the chamber A were evaluated by mass-averaging method. The estimated cycle-averaged pressure ratio became 1.067 means that a pressure gain of 6.7% was obtained in the chamber A. Although the hydrogen fuel mass flow rate in the pulse combustion mode was larger than that in the normal combustion mode, the apparent higher value of specific output power in the pulse combustion mode than in the normal combustion mode demonstrated the feature of pressure-gain combustion.
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Hebrard, P., J. Courquet, and G. Lavergne. "Numerical Simulation of Two-Phase Flow in Combustion Chambers." In ASME 1991 International Gas Turbine and Aeroengine Congress and Exposition. American Society of Mechanical Engineers, 1991. http://dx.doi.org/10.1115/91-gt-112.

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The purpose of this paper is to describe a new approach in which one uses different kinds of post processing to obtain, from 2D or 3D computation codes, the representation of internal flow inside a combustion chamber as an association of elementary reactors (well stirred, plug flow…) To reach this goal and, in order to test this method, different computation codes are used for the gas phase description: mean flow computation or unsteady codes like “R.V.M.” (Random Vortex Method) or “F.C.T.” (Flux corrected transport) - For the liquid phase behaviour, we use to kinds of Lagrangian transport schemes: one purely deterministic is linked to the mean gas flow computation, the second one provides individual instantaneous trajectories. These various approaches are used for two kinds of 2D geometries: the backward facing step and a simplified afterburner geometry. Examples of residence time computations are presented for the liquid and gas phases and the effect of unsteady flow and drop sizes are demonstrated by experimental comparisons.
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Cameretti, Maria Cristina, and Raffaele Tuccillo. "Comparing Different Solutions for the Micro-Gas Turbine Combustor." In ASME Turbo Expo 2004: Power for Land, Sea, and Air. ASMEDC, 2004. http://dx.doi.org/10.1115/gt2004-53286.

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This paper compares different types of combustion chambers for a micro-gas turbine which operates with both different fuels and variations in the inlet air conditions. The combustor types examined cover a wide variety of conditions for the primary combustion, whose fuel/air equivalence ratio ranges from typical lean-premixed levels up to dramatically rich values. The latter is attained in a combustion chamber of the RQL type, while the lean mixture burns in a tubular swirled combustor also equipped with a pilot igniter. The comparison is completed by including an annular combustor with a primary diffusive burner. The CFD based analysis highlights the main differences among the three types of combustors, in terms of temperature and pollutant distributions, and by focusing the attention on the self-ignition occurrence.
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Reports on the topic "Gas turbine combustion chambers"

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Battelle. Gasification Evaluation of Gas Turbine Combustion. Office of Scientific and Technical Information (OSTI), December 2003. http://dx.doi.org/10.2172/828242.

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T.E. Lippert and D.M. Bachovchin. Gas Turbine Reheat Using In-Situ Combustion. Office of Scientific and Technical Information (OSTI), March 2004. http://dx.doi.org/10.2172/993806.

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Newby, R. A., D. M. Bachovchin, and T. E. Lippert. Gas Turbine Reheat Using In-Situ Combustion. Office of Scientific and Technical Information (OSTI), April 2004. http://dx.doi.org/10.2172/993807.

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D.M. Bachovchin and T.E. Lippert. Gas Turbine Reheat Using In-Situ Combustion. Office of Scientific and Technical Information (OSTI), April 2004. http://dx.doi.org/10.2172/993808.

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D.M. Bachovchin, T.E. Lippert, and R.A. Newby P.G.A. Cizmas. GAS TURBINE REHEAT USING IN SITU COMBUSTION. Office of Scientific and Technical Information (OSTI), May 2004. http://dx.doi.org/10.2172/827534.

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Ulerich, Nancy, Getnet Kidane, Christine Spiegelberg, and Nikolai Tevs. Condition Based Monitoring of Gas Turbine Combustion Components. Office of Scientific and Technical Information (OSTI), September 2012. http://dx.doi.org/10.2172/1117202.

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Richards, G. A., R. S. Gemmen, and M. J. Yip. A test device for premixed gas turbine combustion oscillations. Office of Scientific and Technical Information (OSTI), March 1996. http://dx.doi.org/10.2172/379048.

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Price, Jeffrey. Advanced Materials for Mercury 50 Gas Turbine Combustion System. Office of Scientific and Technical Information (OSTI), September 2008. http://dx.doi.org/10.2172/991117.

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LeCren, R. T. Advanced coal-fueled industrial cogeneration gas turbine system -- combustion development. Office of Scientific and Technical Information (OSTI), June 1994. http://dx.doi.org/10.2172/10194323.

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Robert D. Litt, Donald Anson, Elizabeth De Lucia, and James J. Reuther. Addendum to Final Report "Biomass Gasification Evaluation of Gas Turbine Combustion". Office of Scientific and Technical Information (OSTI), October 2003. http://dx.doi.org/10.2172/890023.

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