Relevant bibliographies by topics / Annular gas turbine combustor

Contents

  1. Journal articles
  2. Dissertations / Theses
  3. Books
  4. Book chapters
  5. Conference papers
  6. Reports

Academic literature on the topic 'Annular gas turbine combustor'

Author: Grafiati
Published: 4 June 2021
Last updated: 1 February 2022

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Journal articles on the topic "Annular gas turbine combustor"

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Khandelwal, B., A. Karakurt, V. Sethi, R. Singh, and Z. Quan. "Preliminary design and performance analysis of a low emission aero-derived gas turbine combustor." Aeronautical Journal 117, no. 1198 (2013): 1249–71. http://dx.doi.org/10.1017/s0001924000008848.

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Abstract Modern gas turbine combustor design is a complex task which includes both experimental and empirical knowledge. Numerous parameters have to be considered for combustor designs which include combustor size, combustion efficiency, emissions and so on. Several empirical correlations and experienced approaches have been developed and summarised in literature for designing conventional combustors. A large number of advanced technologies have been successfully employed to reduce emissions significantly in the last few decades. There is no literature in the public domain for providing detail
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Sokolov, K. Y., A. G. Tumanovskiy, M. N. Gutnik, A. V. Sudarev, Y. I. Zakharov, and E. D. Winogradov. "Mathematical Modeling of an Annular Gas Turbine Combustor." Journal of Engineering for Gas Turbines and Power 117, no. 1 (1995): 94–99. http://dx.doi.org/10.1115/1.2812787.

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A mathematical model for the description of axisymmetric swirled flow with diffusion combustion is based on numerical solution of the Reynolds equation with a k–W model of turbulence. The results of numerical and experimental investigations of local and general characteristics of flow, heat and mass transfer, combustion, and NOx formation in an annular combustor with opposite swirled air jets are presented. Satisfactory agreement between calculations and experiments is obtained. The dependences of combustor characteristics versus geometric and operational parameters are generalized.
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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 (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 becom
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Feitelberg, Alan S., Michael D. Starkey, Richard B. Schiefer, et al. "Performance of a Reduced NOx Diffusion Flame Combustor for the MS5002 Gas Turbine." Journal of Engineering for Gas Turbines and Power 122, no. 2 (2000): 301–6. http://dx.doi.org/10.1115/1.483217.

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This paper describes a reduced NOx diffusion flame combustor that has been developed for the MS5002 gas turbine. Laboratory tests have shown that when firing with natural gas, without water or steam injection, NOx emissions from the new combustor are about 40 percent lower than NOx emissions from the standard MS5002 combustor. CO emissions are virtually unchanged at base load, but increase at part load conditions. The laboratory results were confirmed in 1997 by a commercial demonstration test at a British Petroleum site in Prudhoe Bay, Alaska. The standard MS5002 gas turbine is equipped with
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Kadhim, Wael, Dhirgham Alkhafagiy, and Andrew Shires. "Simulation of the flow inside an annular can combustor." International Journal of Engineering & Technology 3, no. 3 (2014): 357. http://dx.doi.org/10.14419/ijet.v3i3.2499.

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In the gas turbine combustion system, the external flows in annuli play one of the key roles in controlling pressure loss, air flow distribution around the combustor liner, and the attendant effects on performance, durability, and stability. This paper describes a computational fluid dynamics (CFD) simulation of the flow in the outer annulus of a can combustor. Validating this simulation was done with experimental results obtained from analyzing the flow inside a can combustor annulus that was used in a Babylon/Iraq gas turbine power station. Pitot static tubes were used to measure the velocit
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Kelsall, G. J., M. A. Smith, and M. F. Cannon. "Low Emissions Combustor Development for an Industrial Gas Turbine to Utilize LCV Fuel Gas." Journal of Engineering for Gas Turbines and Power 116, no. 3 (1994): 559–66. http://dx.doi.org/10.1115/1.2906856.

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Advanced coal-based power generation systems such as the British Coal Topping Cycle offer the potential for high-efficiency electricity generation with minimum environmental impact. An important component of the Topping Cycle program is the gas turbine, for which development of a combustion system to burn low calorific value coal derived fuel gas, at a turbine inlet temperature of 1260°C (2300°F), with minimum pollutant emissions, is a key R&D issue. A phased combustor development program is underway burning low calorific value fuel gas (3.6-4.1 MJ/m3) with low emissions, particularly NOx
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Kim, J., M. G. Dunn, A. J. Baran, D. P. Wade, and E. L. Tremba. "Deposition of Volcanic Materials in the Hot Sections of Two Gas Turbine Engines." Journal of Engineering for Gas Turbines and Power 115, no. 3 (1993): 641–51. http://dx.doi.org/10.1115/1.2906754.

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This paper reports the results of a series of tests designed to determine the melting and subsequent deposition behavior of volcanic ash cloud materials in modern gas turbine engine combustors and high-pressure turbine vanes. The specific materials tested were Mt. St. Helens ash and a soil blend containing volcanic ash (black scoria) from Twin Mountain, NM. Hot section test systems were built using actual engine combustors, fuel nozzles, ignitors, and high-pressure turbine vanes from an Allison T56 engine can-type combustor and a more modern Pratt and Whitney F-100 engine annular-type combusto
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YAHATA, Kazunori, Koji MATSUBARA, Hiroyuki KOSHIKIZAWA, and Kazuyuki ABE. "Numerical Analysis of Annular Combustor for Micro Gas Turbine." Proceedings of Conference of Hokuriku-Shinetsu Branch 2018.55 (2018): D031. http://dx.doi.org/10.1299/jsmehs.2018.55.d031.

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Fureby, Christer. "LES of a Multi-burner Annular Gas Turbine Combustor." Flow, Turbulence and Combustion 84, no. 3 (2009): 543–64. http://dx.doi.org/10.1007/s10494-009-9236-9.

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Garland, R. V., and P. W. Pillsbury. "Status of Topping Combustor Development for Second-Generation Fluidized Bed Combined Cycles." Journal of Engineering for Gas Turbines and Power 114, no. 1 (1992): 126–31. http://dx.doi.org/10.1115/1.2906294.

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Addition of a fluidized bed combustor to a high-efficiency combined cycle plant enables direct firing of inexpensive run-of-the-mine coal in an environmentally acceptable manner. To attain high thermal efficiencies, coal pyrolysis is included. The low heating value fuel gas from the pyrolyzer is burned in a topping combustion system that boosts gas turbine inlet temperature to state of the art while the pyrolyzer-produced char is burned in the bed. The candidate topping combustor, the multi-annular swirl burner, based on a design by J. M. Bee´r, is presented and discussed. Design requirements
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Dissertations / Theses on the topic "Annular gas turbine combustor"

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Carmack, Andrew Cardin. "Heat Transfer and Flow Measurements in Gas Turbine Engine Can and Annular Combustors." Thesis, Virginia Tech, 2012. http://hdl.handle.net/10919/32466.

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A comparison study between axial and radial swirler performance in a gas turbine can combustor was conducted by investigating the correlation between combustor flow field geometry and convective heat transfer at cold flow conditions for Reynolds numbers of 50,000 and 80,000. Flow velocities were measured using Particle Image Velocimetry (PIV) along the center axial plane and radial cross sections of the flow. It was observed that both swirlers produced a strong rotating flow with a reverse flow core. The axial swirler induced larger recirculation zones at both the backside wall and the central
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Tse, David Gar Nile. "Flow and combustion characteristics of model annular and can-type combustors." Thesis, Imperial College London, 1988. http://hdl.handle.net/10044/1/8941.

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Kao, Yi-Huan. "Experimental Investigation of Aerodynamics and Combustion Properties of a Multiple-Swirler Array." University of Cincinnati / OhioLINK, 2014. http://rave.ohiolink.edu/etdc/view?acc_num=ucin1406881553.

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Spencer, A. "Gas turbine combustor port flows." Thesis, Loughborough University, 1998. https://dspace.lboro.ac.uk/2134/6883.

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Competitive pressure and stringent emissions legislation have placed an urgent demand on research to improve our understanding of the gas turbine combustor flow field. Flow through the air admission ports of a combustor plays an essential role in determining the internal flow patterns on which many features of combustor performance depend. This thesis explains how a combination of experimental and computational research has helped improve our understanding, and ability to predict, the flow characteristics of jets entering a combustor. The experiments focused on a simplified generic geometry of
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Asere, Abraham Awolola. "Gas turbine combustor wall cooling." Thesis, University of Leeds, 1986. http://etheses.whiterose.ac.uk/2590/.

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The need for better methods of cooling gas turbine combustors and a review of current cooling techniques have been presented. Three cooling methods are investigated: (a) Full Coverage Discrete Hole Film Cooling (Effusion), (b) Impingement/Effusion Hybrid Cooling Systems, and (c) Transpiration Cooling. The aim of these cooling techniques is to effectively and efficiently cool gas turbine combustors with a significant reduction in current cooling air requirements. The range of test conditions were coolant temperature, Tc, of 289 < Tc 710 K and combustion gases temperature, Tg, of 500 Tg N< 1900
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Murthy, J. N. "Gas turbine combustor modelling for design." Thesis, Cranfield University, 1988. http://hdl.handle.net/1826/2626.

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The design and development of gas turbine combustors is a crucial but uncertain part of an engine development process. Combustion within a gas turbine is a complex interaction of, among other things, fluid dynamics, heat and mass transfer and chemical kinetics. At present, the design process relies upon a wealth of experimental data and correlations. The proper use of this information requires experienced combustion engineers and even for them the design process is very time consuming. Some major engine manufacturers have attempted to address the above problem by developing one dimensional com
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Bengtsson, Karl. "ThermoacousticInstabilities in a Gas Turbine Combustor." Thesis, KTH, MWL Marcus Wallenberg Laboratoriet, 2017. http://urn.kb.se/resolve?urn=urn:nbn:se:kth:diva-226530.

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Stationary gas turbines are widely used today for power generation and mechanical drive applications. The introduction of new regulations on emissions in the last decades have led to extensive development and new technologies used within modern gas turbines. The majority of the gas turbines sold today have a so called DLE (Dry Low Emission) combustion system that mainly operates in the leanpremixed combustion regime. The lean-premixed regime is characterized by low emission capabilities but are more likely to exhibit stability issues compared to traditional non-premixed combustion systems. The
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Main, A. D. J. "Annular turbine cascade aerodynamics." Thesis, University of Oxford, 1994. http://ethos.bl.uk/OrderDetails.do?uin=uk.bl.ethos.239350.

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Poppe, Christian. "Scalar measurements in a gas turbine combustor." Thesis, Imperial College London, 1997. http://ethos.bl.uk/OrderDetails.do?uin=uk.bl.ethos.264987.

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Zheng, Qing-ping. "Soot production in a tubular gas turbine combustor." Thesis, Cranfield University, 1994. http://hdl.handle.net/1826/3910.

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Soot production in gas turbine combustors is not desirable since it is the major source of exhaust smoke emission and its thermal radiation to the combustor liner deteriorates the liner durability. Soot formation involves comparatively slow chemistry and equilibrium can not be applied to soot modelling in the combustor flow field. . The exact sooting process in the combustor is poorly understood given both the complexity and the limited experimental data available. The work reported in this thesis seeks to first develop in-situ techniques for retrieving spatially-resolved soot properties, main
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Books on the topic "Annular gas turbine combustor"

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Melconian, Jerry O. Introducing the VRT gas turbine combustor. NASA, 1990.

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Bennett, J. S. Gas turbine combustor and engine augmentor tube sooting characteristics. Naval Postgraduate School, 1986.

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

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

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Young, Mark F. Measurements of gas turbine combustor and engine augmentor tube sooting characteristics. Naval Postgraduate School, 1988.

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Lin, Chin-Shun. Numerical calculations of turbulent reacting flow in a gas-turbine combustor. National Aeronautics and Space Administration, 1987.

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Paxson, Daniel E. A modified through-flow ware rotor cycle with combustor bypass ducts. National Aeronautics and Space Administration, Lewis Research Center, 1998.

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Paxson, Daniel E. A modified through-flow ware rotor cycle with combustor bypass ducts. National Aeronautics and Space Administration, Lewis Research Center, 1998.

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Paxson, Daniel E. A modified through-flow ware rotor cycle with combustor bypass ducts. National Aeronautics and Space Administration, Lewis Research Center, 1998.

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Tacina, Robert R. Flame tube NOx emissions using a lean-direct-wall-injection combustor concept. National Aeronautics and Space Administration, Glenn Research Center, 2001.

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Book chapters on the topic "Annular gas turbine combustor"

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Fu, Zaiguo, Huanhuan Gao, Lingtong Li, Jiang Liu, Zhuoxiong Zeng, and Jianxing Ren. "Effect of Swirling Strength on Flow Characteristics of a Heavy-Duty Gas Turbine Annular Combustion Chamber." In Computational and Experimental Simulations in Engineering. Springer International Publishing, 2019. http://dx.doi.org/10.1007/978-3-030-27053-7_79.

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Widenhorn, A., B. Noll, and M. Aigner. "Numerical Characterization of a Gas Turbine Model Combustor." In High Performance Computing in Science and Engineering '09. Springer Berlin Heidelberg, 2010. http://dx.doi.org/10.1007/978-3-642-04665-0_13.

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Roshan, Dinesh Kumar, Ramana Sreenivas Burela, and Abhijit Kushari. "Design Philosophy for a Laboratory Scale Gas Turbine Combustor." In Innovations in Sustainable Energy and Cleaner Environment. Springer Singapore, 2019. http://dx.doi.org/10.1007/978-981-13-9012-8_14.

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Shinjo, Jyunji, Yasuhiro Mizobuchi, and Satoru Ogawa. "LES of Unstable Combustion in a Gas Turbine Combustor." In Lecture Notes in Computer Science. Springer Berlin Heidelberg, 2003. http://dx.doi.org/10.1007/978-3-540-39707-6_18.

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Nakamura, Sunao, Katsuya Hyodo, and Osamu Kawaguchi. "Structure of the Primary Region of a Model Gas Turbine Combustor." In Aerothermodynamics in Combustors. Springer Berlin Heidelberg, 1992. http://dx.doi.org/10.1007/978-3-642-84755-4_21.

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Coupland, J., and C. H. Priddin. "Modelling the Flow and Combustion in a Production Gas Turbine Combustor." In Turbulent Shear Flows 5. Springer Berlin Heidelberg, 1987. http://dx.doi.org/10.1007/978-3-642-71435-1_26.

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Indira Priyadarsini, Ch, A. Akhil, and V. Srilaxmi Shilpa. "Non-premixed Combustion Analysis on Micro-Gas Turbine Combustor Using LPG and Natural Gas." In Lecture Notes in Mechanical Engineering. Springer Singapore, 2020. http://dx.doi.org/10.1007/978-981-15-1124-0_6.

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Lisanti, Joel C., and William L. Roberts. "Pulse Combustor Driven Pressure Gain Combustion for High Efficiency Gas Turbine Engines." In Combustion for Power Generation and Transportation. Springer Singapore, 2017. http://dx.doi.org/10.1007/978-981-10-3785-6_7.

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Xiao, Yinli, Zhibo Cao, Changwu Wang, and Wenyan Song. "The Investigation of Fuel Effects on Industrial Gas Turbine Combustor Using OpenFOAM." In Lecture Notes in Electrical Engineering. Springer Singapore, 2019. http://dx.doi.org/10.1007/978-981-13-3305-7_144.

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Fichera, Alberto, Cinzia Losenno, and Arturo Pagano. "Phase Space Description of Unstable Dynamics of a Lean Premixed Gas Turbine Combustor." In New and Renewable Technologies for Sustainable Development. Springer US, 2002. http://dx.doi.org/10.1007/978-1-4615-0296-8_38.

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Conference papers on the topic "Annular gas turbine combustor"

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Cai, Jun, Fumitaka Ichihashi, Bassam Mohammad, Samir Tambe, Yi-Huan Kao, and San-Mou Jeng. "Gas Turbine Single Annular Combustor Sector: Combustion Dynamics." In 48th AIAA Aerospace Sciences Meeting Including the New Horizons Forum and Aerospace Exposition. American Institute of Aeronautics and Astronautics, 2010. http://dx.doi.org/10.2514/6.2010-21.

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Mohammad, Bassam, Jun Cai, and San-Mou Jeng. "Gas Turbine Single Annular Combustor Sector Aerodynamics." In 48th AIAA Aerospace Sciences Meeting Including the New Horizons Forum and Aerospace Exposition. American Institute of Aeronautics and Astronautics, 2010. http://dx.doi.org/10.2514/6.2010-579.

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Sokolov, K. Y., A. G. Tumanovskiy, M. N. Gutnik, A. V. Sudarev, Y. I. Zakharov, and E. D. Winogradov. "Mathematical Modelling of an Annular Gas Turbine Combustor." 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-339.

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Mathematical model for description of axisymmetric swirled flow with diffusion combustion is based on numerical solution of Reynolds equation with k-W modell of turbulence. The results of numerical and experimental investigations of local and general characteristicse of flow, heat and mass transfer, combustion and NOx formation in annular combustor with opposite swirled air jets are presented. Satisfactory agreement between calculations and experiments is obtained. The dependences of combustor characteristics vs geometric and operational parameters are generalized.
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Ichihashi, Fumitaka, Jun Cai, Y. H. Kao, A. A. Syed, and S. M. Jeng. "Combustion Dynamics in a Gas Turbine Single Annular Combustor Sector." In ASME Turbo Expo 2010: Power for Land, Sea, and Air. ASMEDC, 2010. http://dx.doi.org/10.1115/gt2010-23587.

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The occurrence of combustion instability dynamics known, as “screech, howl and growl,” in the combustors of gas turbine engines is a very difficult challenge for engineers. The very high amplitude pressure oscillations caused by combustion dynamics, are not only detrimental to the operation of the engine and combustor, but the difficulty in predicting and remedying these problems can lead to significant costs and delays in engine development. The coupling of the unsteady heat release in the flame with the natural acoustic resonance modes of the combustor duct causes the phenomena of combustion
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Di Martino, P., and G. Cinque. "Numerical Simulation of an Annular Combustor." 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-182.

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A numerical model to solve three-dimensional turbulent reactive flows in arbitrary shapes is presented. The conservative form of the primitive-variable formulation of steady density-weighted Navier Stokes equations written for a general curvilinear system is adopted. Turbulent transport is described by the k-ε model. The reactions associated with heat release are assumed sufficiently fast for chemical equilibrium to prevail on an instantaneous basis and the influence of local turbulent fluctuations in mixture strenght accounted for by a β-probability density function. The numerical scheme is b
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Bhattacharya, Arijit, Bikash Gupta, Satyajit Hansda, et al. "Lean Blowout Phenomena and Prior Detection of Lean Blowout in a Premixed Model Annular Combustor." In ASME 2019 Gas Turbine India Conference. American Society of Mechanical Engineers, 2019. http://dx.doi.org/10.1115/gtindia2019-2491.

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Abstract Strict emission norms in the last few decades have paved the path for adaptation of new low NoX emission alternatives to power generation and aircraft propulsion. Lean combustion is a very promising and practicable technology for reducing NOX reduction and also have very high fuel efficiency. However, lean combustion technology suffers from inherent combustion instabilities that are manifested under different conditions, most importantly, thermoacoustic instability and lean blowout. Lean blowout occurs when a gas turbine combustor operating close to lean limit, for lowest NoX emission
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Cronemyr, Peter J. M., Chris J. Hulme, and Christian Troger. "Coupled Acoustic-Structure Analysis of an Annular DLE Combustor." 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-502.

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With the advent of today’s dry low emission (DLE) combustors for industrial gas turbines (GT), an additional type of load case other than thermal loading on the combustor structure, has put itself heavily into focus, namely pulsation loading. Although recognised for decades in rocket engines and ram-jets, it was not until the incorporation of diluted flames and completely closed combustors, used to reduce NOx emissions, that thermo-acoustically excited pressure pulsations became an issue in the design of industrial GT combustors. This paper presents the computational methods that are available
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Ruedel, Uwe, Bogdan Trbojevic, Urs Benz, Martin Zajadatz, and Klaus Doebbeling. "Development of an Annular Combustor Chamber." In ASME Turbo Expo 2013: Turbine Technical Conference and Exposition. American Society of Mechanical Engineers, 2013. http://dx.doi.org/10.1115/gt2013-95495.

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To accommodate the customer’s expectations for operational flexibility and low power generation costs, a gas turbine has to be robust, flexible and cost effective. Since its introduction in 1993 and with its more than 7.5 million operating hours and over 54’000 starts, the GT13E2 gas turbine has already demonstrated to be a most flexible and reliable engine. It is being used in connection with many different applications, and meets a very broad range of environment and operation conditions. The GT13E2 upgrade 2012 described in this paper further improves these capabilities. The next generation
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Smiljanovski, Vanco, and Norbert Brehm. "CFD Liquid Spray Combustion Analysis of a Single Annular Gas Turbine Combustor." 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-300.

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In this paper CFD analysis of the steady two-phase turbulent combusting flow in a single annular low-NOx combustor is presented. For this purpose the commercial code CFD-ACE (1998) was used, where Eulerian equations are solved for the gas phase and the liquid spray fuel droplets are treated in a Lagrangian frame of reference allowing for evaporation of droplets and providing source terms for the gas phase. The standard k-ε model was used for turbulence and an assumed shape probability density function was used for the instantaneous chemistry in the conserved scalar combustion model. Thermal NO
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Chow, S. K., and J. J. McGuirk. "Numerical Prediction of Flow and Combustion Characteristics of a Model Annular Combustor." 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-364.

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Two instantaneous chemistry descriptions (full chemical equilibrium and laminar flamelet) were applid to the prediction of gaseous reaction in a small-scale combustor. The chemical state relationships were combined with a single conserved scalar/β-function pdf/k-ε turbulence model closure. Encouraging results were obtained for the flowfield and conserved scalar distributions, although only when the jet entry boundary conditions were altered to accord closely with several expected experimental features. These predictions imply that any acceptable approach to combustor modelling must extend calc
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Reports on the topic "Annular gas turbine combustor"

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Etemad, Shahrokh, Benjamin Baird, Sandeep Alavandi, and William Pfefferle. Industrial Gas Turbine Engine Catalytic Pilot Combustor-Prototype Testing. Office of Scientific and Technical Information (OSTI), 2010. http://dx.doi.org/10.2172/1051563.

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Huang, Cheng, Rohan Gejji, William Anderson, Changjin Yoon, and Venkateswaran Sankaran. Combustion Dynamics Behavior in a Single-Element Lean Direct Injection (LDI) Gas Turbine Combustor. Defense Technical Information Center, 2014. http://dx.doi.org/10.21236/ada611210.

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Huang, Cheng, Rohan Gejji, William E. Anderson, and Venkateswaran Sankaran. Effects of Fuel Spray Modeling on Combustion Instability Predictions in a Single-Element Lean Direct Injection (LDI) Gas Turbine Combustor. Defense Technical Information Center, 2014. http://dx.doi.org/10.21236/ada623017.

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Ragland, K. W., D. J. Aerts, and C. A. Palmer. Development of a gravel bed combustor for a solid fueled gas turbine for the period February 1, 1989 to June 30, 1991. Office of Scientific and Technical Information (OSTI), 1992. http://dx.doi.org/10.2172/41336.

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Utilization of coal mine ventilation exhaust as combustion air in gas-fired turbines for electric and/or mechanical power generation. Semi-annual topical report, June 1995--August 1995. Office of Scientific and Technical Information (OSTI), 1995. http://dx.doi.org/10.2172/393338.

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