Relevant bibliographies by topics / Gas Turbine Engine Combustion

Academic literature on the topic 'Gas Turbine Engine Combustion'

Author: Grafiati
Published: 10 December 2022
Last updated: 28 January 2023

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Journal articles on the topic "Gas Turbine Engine Combustion"

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Agbadede, Roupa, and Biweri Kainga. "Effect of Water Injection into Aero-derivative Gas Turbine Combustors on NOx Reduction." European Journal of Engineering Research and Science 5, no. 11 (November 21, 2020): 1357–59. http://dx.doi.org/10.24018/ejers.2020.5.11.2180.

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Oxides of Nitrogen (NOx) generated from gas turbines causes enormous harm to human health and the environment. As a result, different methods have been employed to reduce NOx produced from gas turbine combustion process. One of such technique is the injection of water or steam into the combustion chamber to reduce the flame temperature. A twin shaft aero-derivative gas turbine was modelled and simulated using GASTURB simulation software. The engine was modelled after the GE LM2500 class of gas turbine engines. Water injection into the gas turbine combustor was simulated by implanting water-to-fuel ratios of 0 to 0.8, in an increasing order of 0.2. The results show that when water-to-fuel ratio was increased, the Nox severity index reduced. While heat rate and fuel flow increased with water-to-fuel ratio (injection flow rate).
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Agbadede, Roupa, and Isaiah Allison. "Effect of Water Injection into Aero-derivative Gas Turbine Combustors on NOx Reduction." European Journal of Engineering and Technology Research 5, no. 11 (November 21, 2020): 1357–59. http://dx.doi.org/10.24018/ejeng.2020.5.11.2180.

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Oxides of Nitrogen (NOx) generated from gas turbines causes enormous harm to human health and the environment. As a result, different methods have been employed to reduce NOx produced from gas turbine combustion process. One of such technique is the injection of water or steam into the combustion chamber to reduce the flame temperature. A twin shaft aero-derivative gas turbine was modelled and simulated using GASTURB simulation software. The engine was modelled after the GE LM2500 class of gas turbine engines. Water injection into the gas turbine combustor was simulated by implanting water-to-fuel ratios of 0 to 0.8, in an increasing order of 0.2. The results show that when water-to-fuel ratio was increased, the Nox severity index reduced. While heat rate and fuel flow increased with water-to-fuel ratio (injection flow rate).
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Zhu, Dengting, Zhenzhong Sun, and Xinqian Zheng. "Turbocharging strategy among variable geometry turbine, two-stage turbine, and asymmetric two-scroll turbine for energy and emission in diesel engines." Proceedings of the Institution of Mechanical Engineers, Part A: Journal of Power and Energy 234, no. 7 (November 28, 2019): 900–914. http://dx.doi.org/10.1177/0957650919891355.

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Energy saving and emission reduction are very urgent for internal combustion engines. Turbocharging and exhaust gas recirculation technologies are very significant for emissions and fuel economy of internal combustion engines. Various after-treatment technologies in internal combustion engines have different requirements for exhaust gas recirculation rates. However, it is not clear how to choose turbocharging technologies for different exhaust gas recirculation requirements. This work has indicated the direction to the turbocharging strategy among the variable geometry, two-stage, and asymmetric twin-scroll turbocharging for different exhaust gas recirculation rates. In the paper, a test bench engine experiment was presented to validate the numerical models of the three diesel engines employed with the asymmetric twin-scroll turbine, two-stage turbine, and variable geometry turbine. On the basis of the numerical models, the turbocharging routes among the three turbocharging approaches under different requirements for EGR rates are studied, and the other significant performances of the three turbines were also discussed. The results show that there is an inflection point in the relative advantages of asymmetric, variable geometry, and two-stage turbocharged engines. At the full engine load, when the EGR rate is lower than 29%, the two-stage turbocharging technology has the best performances. However, when the exhaust gas recirculation rate is higher than 29%, the asymmetric twin-scroll turbocharging is the best choice and more appropriate for driving high exhaust gas recirculation rates. The work may offer guidelines to choose the most suitable turbocharging technology for engine engineers and manufacturers to achieve further improvements in engine energy and emissions.
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Chand, Dharmahinder Singh, Daamanjyot Barara, Gautam Ganesh, and Suraj Anand. "Comparison of Efficiency of Conventional Shaped Circular and Elliptical Shaped Combustor." MATEC Web of Conferences 151 (2018): 02002. http://dx.doi.org/10.1051/matecconf/201815102002.

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There have been concerted efforts towards improving the fuel efficiency of the jet engines in the past, with an aim of reducing the incomplete combustion. The process of combustion in a jet engine takes place in the combustor. A study was conducted for enhancement of air-fuel mixing process by computational analysis of an elliptically shaped combustor for a gas turbine engine. The results of computational analysis of an elliptical shape combustor were compared with a circular shape combustor used in gas turbine engines with a identical cross sectional area. The comparison of the computationally derived parameters of the two combustors i.e. temperature, pressure, and velocity are studied and analyzed. The study intends towards the comparison of the combustion efficiencies of the circular and elliptically shaped combustors. The combustion efficency of elliptical chamber is found to be 98.72% at the same time it was observed 56.26% in case of circular type combustor.
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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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Jansen, M., T. Schulenberg, and D. Waldinger. "Shop Test Result of the V64.3 Gas Turbine." Journal of Engineering for Gas Turbines and Power 114, no. 4 (October 1, 1992): 676–81. http://dx.doi.org/10.1115/1.2906641.

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The V64.3 60-MW combustion turbine is the first of a new generation of high-temperature gas turbines, designed for 50 and 60 Hz simple cycle, combined cycle, and cogeneration applications. The prototype engine was tested in 1990 in the Berlin factories under the full range of operation conditions. It was equipped with various measurement systems to monitor pressures, gas and metal temperatures, clearances, strains, vibrations, and exhaust emissions. The paper describes the engine design, the test facility and instrumentation, and the engine performance. Results are given for turbine blade temperatures, compressor and turbine vibrations, exhaust gas temperature, and NOx emissions for combustion of natural gas and fuel oil.
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Hutchins, T. E., and M. Metghalchi. "Energy and Exergy Analyses of the Pulse Detonation Engine." Journal of Engineering for Gas Turbines and Power 125, no. 4 (October 1, 2003): 1075–80. http://dx.doi.org/10.1115/1.1610015.

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Energy and exergy analyses have been performed on a pulse detonation engine. A pulse detonation engine is a promising new engine, which uses a detonation wave instead of a deflagration wave for the combustion process. The high-speed supersonic combustion wave reduces overall combustion duration resulting in an nearly constant volume energy release process compared to the constant pressure process of gas turbine engines. Gas mixture in a pulse detonation engine has been modeled to execute the Humphrey cycle. The cycle includes four processes: isentropic compression, constant volume combustion, isentropic expansion, and isobaric compression. Working fluid is a fuel-air mixture for unburned gases and products of combustion for burned gases. Different fuels such as methane and JP10 have been used. It is assumed that burned gases are in chemical equilibrium states. Both thermal efficiency and effectiveness (exergetic efficiency) have been calculated for the pulse detonation engine and simple gas turbine engine. Comparison shows that for the same pressure ratio pulse detonation engine has better efficiency and effectiveness than the gas turbine system.
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Sarkar, Asis. "A TOPSIS method to evaluate the technologies." International Journal of Quality & Reliability Management 31, no. 1 (December 20, 2013): 2–13. http://dx.doi.org/10.1108/ijqrm-03-2013-0042.

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Purpose – This paper aims to evaluate nine types of electrical energy generation options with regard to seven criteria. The analytic hierarchy process (AHP) was used to perform the evaluation. The TOPSIS method was used to evaluate the best generation technology. Design/methodology/approach – The options that were evaluated are the hydrogen combustion turbine, the hydrogen internal combustion engine, the hydrogen fuelled phosphoric acid fuel cell, the hydrogen fuelled solid oxide fuel cell, the natural gas fuelled phosphoric acid fuel cell, the natural gas fuelled solid oxide fuel cell, the natural gas turbine, the natural gas combined cycle and the natural gas internal combustion engine. The criteria used for the evaluation are CO2 emissions, NOX emissions, efficiency, capital cost, operation and maintenance costs, service life and produced electricity cost. Findings – The results drawn from the analysis in technology wise are as follows: natural gas fuelled solid oxide fuel cells>natural gas combined cycle>natural gas fuelled phosphoric acid fuel cells>natural gas internal combustion engine>hydrogen fuelled solid oxide fuel cells>hydrogen internal combustion engines>hydrogen combustion turbines>hydrogen fuelled phosphoric acid fuel cells> and natural gas turbine. It shows that the natural gas fuelled solid oxide fuel cells are the best technology available among all the available technology considering the seven criteria such as service life, electricity cost, O&M costs, capital cost, NOX emissions, CO2 emissions and efficiency of the plant. Research limitations/implications – The most dominant electricity generation technology proved to be the natural gas fuelled solid oxide fuel cells which ranked in the first place among nine alternatives. The research is helpful to evaluate the different alternatives. Practical implications – The research is helpful to evaluate the different alternatives and can be extended in all the spares of technologies. Originality/value – The research was the original one. Nine energy generation options were evaluated with regard to seven criteria. The energy generation options were the hydrogen combustion turbine, the hydrogen internal combustion engine, the hydrogen fuelled phosphoric acid fuel cell, the hydrogen fuelled solid oxide fuel cell, the natural gas fuelled phosphoric acid fuel cell, the natural gas fuelled solid oxide fuel cell, the natural gas turbine, the natural gas combined cycle and the natural gas internal combustion engine. The criteria used for the evaluation were efficiency, CO2 emissions, NOX emissions, capital cost, O&M costs, electricity cost and service life.
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Langston, Lee S. "Breaking the Barriers." Mechanical Engineering 134, no. 05 (May 1, 2012): 32–37. http://dx.doi.org/10.1115/1.2012-may-2.

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This article explores the new developments in the field of gas turbines and the recent progress that has been made in the industry. The gas turbine industry has had its ups and downs over the past 20 years, but the production of engines for commercial aircraft has become the source for most of its growth of late. Pratt & Whitney’s recent introduction of its new geared turbofan engine is an example of the primacy of engine technology in aviation. Many advances in commercial aviation gas turbine technology are first developed under military contracts, since jet fighters push their engines to the limit. Distributed generation and cogeneration, where the exhaust heat is used directly, are other frontiers for gas turbines. Work in fluid mechanics, heat transfer, and solid mechanics has led to continued advances in compressor and turbine component performance and life. In addition, gas turbine combustion is constantly being improved through chemical and fluid mechanics research.
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Langston, Lee S. "Riding the Surge." Mechanical Engineering 135, no. 05 (May 1, 2013): 37–41. http://dx.doi.org/10.1115/1.2013-may-2.

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This article explores the advantages of gas turbines in the marine industry. Marine gas turbines, which are designed specifically for use on ships, have long been one of the segments of the gas turbine market. One advantage that gas turbines have over conventional marine diesels is volume. Gas turbines are the prime movers for the modern combined cycle electric power plant. Both CFM International (a joint venture of General Electric and France’s Snecma) and Pratt & Whitney are working on new engines for this multibillion dollar single-aisle, narrow-body market. Pratt & Whitney’s new certified PW1500G geared turbofans will have a first flight powering the first Bombardier CSeries aircraft. On land, sea, and air, the surge in gas turbine production is remarkable. The experts suggest that what the steam engine was to the 19th century and the internal combustion engine was to the 20th, the gas turbine might be to the 21st century: the ubiquitous prime mover of choice.
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Dissertations / Theses on the topic "Gas Turbine Engine Combustion"

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Ahmad, N. T. "Swirl stabilised gas turbine combustion." Thesis, University of Leeds, 1986. http://ethos.bl.uk/OrderDetails.do?uin=uk.bl.ethos.356423.

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Perry, Matthew Vincent. "An Investigation of Lean Premixed Hydrogen Combustion in a Gas Turbine Engine." Thesis, Virginia Tech, 2009. http://hdl.handle.net/10919/43532.

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As a result of growing concerns about the carbon emissions associated with the combustion of conventional hydrocarbon fuels, hydrogen is gaining more attention as a clean alternative. The combustion of hydrogen in air produces no carbon emissions. However, hydrogen-air combustion does have the potential to produce oxides of nitrogen (NOx), which are harmful pollutants. The production of NOx can be significantly curbed using lean premixed combustion, wherein hydrogen and air are mixed at an equivalence ratio (the ratio of stoichiometric to actual air in the combustion process) significantly less than 1.0 prior to combustion. Hydrogen is a good candidate for use in lean premixed systems due to its very wide flammability range. The potential for the stable combustion of hydrogen at a wide range of equivalence ratios makes it particularly well-suited to application in gas turbines, where the equivalence ratio is likely to vary significantly over the operating range of the machine.

The strong lean combustion stability of hydrogen-air flames is due primarily to high reaction rates and the associated high turbulent burning velocities. While this is advantageous at low equivalence ratios, it presents a significant danger of flashbackâ the upstream propagation of the flame into the premixing deviceâ at higher equivalence ratios. An investigation has been conducted into the operation of a specific hydrogen-air premixer design in a gas turbine engine. Laboratory tests were first conducted to determine the upper stability limits of a single premixer. Tests were then carried out in which eighteen premixers and a custom-fabricated combustor liner were installed in a modified Pratt and Whitney Canada PT6A-20 turboprop engine. The tests examined the premixer and engine operability as a result of the modifications. A computer cycle analysis model was created to help analyze and predict the behavior of the modified engine and premixers. The model, which uses scaled component maps to predict off-design engine performance, was integral in the analysis of premixer flashback which limited the operation of the modified engine.
Master of Science

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MacCallum, N. R. L. "Studies in gas turbine performance and in combustion." Thesis, University of Glasgow, 2000. http://theses.gla.ac.uk/5335/.

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Ghulam, Mohamad. "Characterization of Swirling Flow in a Gas Turbine Fuel Injector." University of Cincinnati / OhioLINK, 2019. http://rave.ohiolink.edu/etdc/view?acc_num=ucin1563877023803877.

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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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Peck, Jhongwoo 1976. "Development of a catalytic combustion system for the MIT Micro Gas Turbine Engine." Thesis, Massachusetts Institute of Technology, 2003. http://hdl.handle.net/1721.1/28292.

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Thesis (S.M.)--Massachusetts Institute of Technology, Dept. of Aeronautics and Astronautics, 2003.
Includes bibliographical references (p. 71-72).
As part of the MIT micro-gas turbine engine project, the development of a hydrocarbon-fueled catalytic micro-combustion system is presented. A conventionally-machined catalytic flow reactor was built to simulate the micro-combustor and to better understand the catalytic combustion at micro-scale. In the conventionally-machined catalytic flow reactor, catalytic propane/air combustion was achieved over platinum. A 3-D finite element heat transfer model was also developed to assess the heat transfer characteristics of the catalytic micro-combustor. It has been concluded that catalytic combustion in the micro-combustor is limited by diffusion of fuel into the catalyst surface. To address this issue, a catalytic structure with larger surface area was suggested and tested. It was shown that the larger surface area catalyst increased the chemical efficiency. Design guidelines for the next generation catalytic micro-combustor are presented as well.
by Jhongwoo Peck.
S.M.
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Hinse, Mathieu. "Investigation of Transpiration Cooling Film Protection for Gas Turbine Engine Combustion Liner Application." Thesis, Université d'Ottawa / University of Ottawa, 2021. http://hdl.handle.net/10393/42425.

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Transpiration cooling as potential replacement of multi-hole effusion cooling for gas turbine engines combustion liner application is investigated by comparing their cooling film effectiveness based on the mass transfer analogy (CFEM). Pressure sensitive paint was used to measure CFEM over PM surfaces which was found to be on average 40% higher than multi-hole effusion cooling. High porosity PM with low resistance to flow movement were found to offer uneven distribution of exiting coolant, with large amounts leaving the trailing edge, leading to lopsided CFEM. Design of anisotropic PM based on PM properties (porosity, permeability, and inertia coefficient) were investigated using numerical models to obtain more uniform CFEM. Heat transfer analysis of different PM showed that anisotropic samples offered better thermal protection over isotropic PM for the same porosity. Comparison between cooling film effectiveness obtained from temperatures CFET against CFEM revealed large differences in the predicted protection. This is attributed to the assumptions made to apply CFEM, nonetheless, CFEM remains a good proxy to study and improve transpiration cooling. A method for creating a CAD model of designed PM is proposed based on critical characteristics of transpiration cooling for future use in 3D printing manufacturing.
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Manners, A. P. "The calculation of the flows in gas turbine combustion systems." Thesis, Imperial College London, 1998. http://hdl.handle.net/10044/1/8397.

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Villarreal, Daniel Christopher. "Digital Fuel Control for a Lean Premixed Hydrogen-Fueled Gas Turbine Engine." Thesis, Virginia Tech, 2009. http://hdl.handle.net/10919/34974.

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Hydrogen-powered engines have been gaining increasing interest due to the global concerns of the effects of hydrocarbon combustion on climate change. Gas turbines are suitable for operation on hydrogen fuel. This thesis reports the results of investigations of the special requirements of the fuel controller for a hydrogen gas turbine. In this investigation, a digital fuel controller for a hydrogen-fueled modified Pratt and Whitney PT6A-20 turboprop engine was successfully designed and implemented. Included in the design are safety measures to protect the operating personnel and the engine. A redundant fuel control is part of the final design to provide a second method of managing the engine should there be a malfunction in any part of the primary controller.

Parallel to this study, an investigation of the existing hydrogen combustor design was performed to analyze the upper stability limits that were restricting the operability of the engine. The upstream propagation of the flame into the premixer, more commonly known as a flashback, routinely occurred at 150 shaft horsepower during engine testing. The procedures for protecting the engine from a flashback were automated within the fuel controller, significantly reducing the response time from the previous (manual) method. Additionally, protection measures were added to ensure the inter-turbine temperature of the engine did not exceed published limits. Automatic engine starting and shutdown procedures were also added to the control logic, minimizing the effort needed by the operator. The tested performance of the engine with each of the control functions demonstrated the capability of the controller.

Methods to generate an engine-specific fuel control map were also studied. The control map would not only takes into account the operability limits of the engine, but also the stability limits of the premixing devices. Such a map is integral in the complete design of the engine fuel controller.
Master of Science

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Skidmore, F. W., and n/a. "The influence of gas turbine combustor fluid mechanics on smoke emissions." Swinburne University of Technology, 1988. http://adt.lib.swin.edu.au./public/adt-VSWT20070420.131227.

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This thesis describes an experimental program covering the development of certain simple combustion chamber modifications to alleviate smoke emissions from the Allison T56 turboprop engines operated by the Royal Australian Air Force. The work includes a literature survey, smoke emission tests on two variants of the T56 engine, flow visualisation studies of the combustion system in a water tunnel and combustion rig tests of a standard combustor and four possible modifications. The rig tests showed that reductions in smoke emissions of 80% were possible by simple modifications that reduced the primary zone equivalence ratio and improved mixing in that zone.
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Books on the topic "Gas Turbine Engine Combustion"

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Lieuwen, Timothy C., and Vigor Yang. Combustion Instabilities In Gas Turbine Engines. Reston ,VA: American Institute of Aeronautics and Astronautics, 2006. http://dx.doi.org/10.2514/4.866807.

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North Atlantic Treaty Organization. Advisory Group for Aerospace Research and Development. Combustion and fuels in gas turbine engines. Neuilly sur Seine, France: AGARD, 1988.

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North Atlantic Treaty Organization. Advisory Group for Aerospace Research and Development. Combustion and fuels in gas turbine engines. Neuilly sur Seine, France: AGARD, 1988.

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

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

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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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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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Book chapters on the topic "Gas Turbine Engine Combustion"

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Decher, Reiner. "Other Components of the Jet Engine." In The Vortex and The Jet, 125–35. Singapore: Springer Singapore, 2022. http://dx.doi.org/10.1007/978-981-16-8028-1_12.

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AbstractThecompressor may be the challenging component of a gas turbine engine, a combustor and a turbine also must function efficiently. The design aspects of these two components are described here together with how the engine is configured and works as a system.
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Muduli, S. K., R. K. Mishra, and P. C. Mishra. "Computational Study of Combustion Process in a Gas Turbine Engine." In Recent Advances in Thermofluids and Manufacturing Engineering, 139–50. Singapore: Springer Nature Singapore, 2022. http://dx.doi.org/10.1007/978-981-19-4388-1_13.

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Müller, S. H. R., B. Böhm, and A. Dreizler. "High-Speed Laser Diagnostics for the Investigation of Cycle-to-Cycle Variations of IC Engine Processes." In Flow and Combustion in Advanced Gas Turbine Combustors, 463–77. Dordrecht: Springer Netherlands, 2012. http://dx.doi.org/10.1007/978-94-007-5320-4_16.

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Eckbreth, Alan C. "Laser Diagnostics for Gas Turbine Thermometry and Species Measurements." In Instrumentation for Combustion and Flow in Engines, 69–106. Dordrecht: Springer Netherlands, 1989. http://dx.doi.org/10.1007/978-94-009-2241-9_4.

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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, 127–52. Singapore: Springer Singapore, 2017. http://dx.doi.org/10.1007/978-981-10-3785-6_7.

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Dimitrova, D., M. Braun, J. Janicka, and A. Sadiki. "Large Eddy Simulation of Dispersed Two-Phase Flows and Premixed Combustion in IC-Engines." In Flow and Combustion in Advanced Gas Turbine Combustors, 415–44. Dordrecht: Springer Netherlands, 2012. http://dx.doi.org/10.1007/978-94-007-5320-4_14.

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Balijepalli, Ramakrishna, Abhishek Dasore, Upendra Rajak, Y. Siva Kumar Reddy, and Tikendra Nath Varma. "Design and Optimisation of Annulus Combustion Chamber of Gas Turbine Engine: An Analytical and Numerical Approach." In Lecture Notes in Mechanical Engineering, 553–67. Singapore: Springer Singapore, 2022. http://dx.doi.org/10.1007/978-981-16-8341-1_47.

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Singaravelu, Balasubramanian, Sathesh Mariappan, and Avijit Saha. "Theoretical Formulation for the Investigation of Acoustic and Entropy-Driven Combustion Instabilities in Gas Turbine Engines." In Combustion for Power Generation and Transportation, 169–96. Singapore: Springer Singapore, 2017. http://dx.doi.org/10.1007/978-981-10-3785-6_9.

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Dascomb, John, and Anjaneyulu Krothapalli. "Hydrogen-Enriched Syngas from Biomass Steam Gasification for Use in Land-Based Gas Turbine Engines." In Novel Combustion Concepts for Sustainable Energy Development, 89–110. New Delhi: Springer India, 2014. http://dx.doi.org/10.1007/978-81-322-2211-8_6.

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Scharnell, Lennart, and Stuart Sabol. "Gas Turbine Combustion." In Practical Dispute Resolution, 2–4. Cham: Springer International Publishing, 2018. http://dx.doi.org/10.1007/978-3-031-01493-2_2.

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Conference papers on the topic "Gas Turbine Engine Combustion"

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Schlein, Barry. "Gas Turbine Combustion Efficiency." In ASME 1985 Beijing International Gas Turbine Symposium and Exposition. American Society of Mechanical Engineers, 1985. http://dx.doi.org/10.1115/85-igt-121.

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A method of correlating combustor efficiency as a function of geometry and operating conditions is presented. A simple equation correlates all the data for a given engine type with a single parameter. The correlating parameter is a function of fuel flow, pressure, temperature and volume in a form similar to others in the literature. The unique feature of the correlating parameter is its use of internal gas temperature rather than the commonly used combustor inlet temperature. The result is an equation requiring an iterative solution since combustion efficiency is a part of the correlating parameter. With use of a computer this is easily handled. The correlation fits engine data over all flight conditions from high altitude, high Mach number to sea level idle. The correlation is compared to engine test data for several engines.
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Hintz, Douglas E. "The 501D5A Combustion Turbine." 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-267.

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Westinghouse is now offering its latest upgrade of the 501D5 family of combustion turbines. This upgrade engine, designated 501D5A, is based on recent technical advancements successfully incorporated in the 251B12 and 701DA engines. These advancements primarily focus on compressor end modifications for increased mass flow and turbine end modifications for a modest increase in rotor inlet temperature. In addition, modifications were made to the combustion section for use of low emissions combustion systems. This paper will describe these changes incorporated in the upgraded 501D5, along with improvements associated with engine efficiency, which have resulted in an engine with over 10 percent increased power and over 2 percent improved simple cycle heat rate.
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Scarinci, Thomas, and John L. Halpin. "Industrial Trent Combustor — Combustion Noise Characteristics." 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-009.

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Thermoacoustic resonance is a difficult technical problem that is experienced by almost all lean-premixed combustors. The Industrial Trent combustor is a novel dry-low-emissions (DLE) combustor design, which incorporates three stages of lean premixed fuel injection in series. The three stages in series allow independent control of two stages — the third stage receives the balance of fuel to maintain the desired power level — at all power conditions. Thus, primary zone and secondary zone temperatures can be independently controlled. This paper examines how the flexibility offered by a 3-stage lean premixed combustion system permits the implementation of a successful combustion noise avoidance strategy at all power conditions and at all ambient conditions. This is because at a given engine condition (power level and day temperature) a characteristic “noise map” can be generated on the engine, independently of the engine running condition. The variable distribution of heat release along the length of the combustor provides an effective mechanism to control the amplitude of longitudinal resonance modes of the combustor. This approach has allowed the Industrial Trent combustion engineers to thoroughly “map out” all longitudinal combustor acoustic modes and design a fuel schedule that can navigate around regions of combustor thermoacoustic resonance. Noise mapping results are presented in detail, together with the development of noise prediction methods (frequency and amplitude) that have allowed the noise characteristics of the engine to be established over the entire operating envelope of the engine.
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Hou, Xingxia, Shaolin Wang, Pengfu Xie, Qing Gao, Chunqing Tan, and Jianwen Wang. "CFD Simulation of Combustion in Gas Turbine Engine." In 2017 5th International Conference on Frontiers of Manufacturing Science and Measuring Technology (FMSMT 2017). Paris, France: Atlantis Press, 2017. http://dx.doi.org/10.2991/fmsmt-17.2017.170.

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Guillou, Erwann, Ephraim Gutmark, and Michael Cornwell. "Application of Flameless Combustion for Gas Turbine Engine." In 47th AIAA Aerospace Sciences Meeting including The New Horizons Forum and Aerospace Exposition. Reston, Virigina: American Institute of Aeronautics and Astronautics, 2009. http://dx.doi.org/10.2514/6.2009-225.

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Sun, Tao, Minghui Yuan, Yuehan Xu, Guohui Wang, and Nan Ye. "Study of New Exhaust Ejector for Marine Gas Turbine." In ASME 2014 Internal Combustion Engine Division Fall Technical Conference. American Society of Mechanical Engineers, 2014. http://dx.doi.org/10.1115/icef2014-5482.

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With the development at infrared guidance weapon, the survival of the ship, especially in high risk areas, is facing serious challenges. In order to improve its survival ability, infrared suppression system emerges. Marine gas turbine exhaust ejector system is its core component, which is responsible for reducing or even eliminating the infrared radiation signal of marine gas turbine exhaust system. Based on collecting data on many sorts of ejectors, we sort out literature related to gas turbine exhaust ejector. From the view of ejector structure, the paper briefly describes the development of gas turbine exhaust ejector used on ships in domestic and foreign. Put forward two major structural innovations: the structure of nozzle changes from circular to rectangular and diffuser adopts multilevel structure. A new type of marine gas turbine exhaust ejector was designed. Ejector model is simplified. Use numerical simulation method to predict the single stage ejector and multi-stage ejectors. Further structural optimization plan and design can be made based on this essay.
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Narayana Rao, Korukonda Venkata Lakshmi, B. V. S. S. S. Prasad, Ch Kanna Babu, and Girish K. Degaonkar. "Numerical and Experimental Investigations on Liner Heat Transfer in an Aero Engine Combustion Chamber." In ASME 2017 Gas Turbine India Conference. American Society of Mechanical Engineers, 2017. http://dx.doi.org/10.1115/gtindia2017-4776.

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The Gas turbine combustion chamber is the highest thermally loaded component where the temperature of the combustion gases is higher than the melting point of the liner that confines the gases. Combustor liner temperatures have to be evaluated at all the operating conditions in the operating envelope to ensure a satisfactory liner life and structural integrity. On experimental side the combustion chamber rig testing involves a lot of time and is very expensive, while the numerical computations and simulations has to be validated with the experimental results. This paper is mainly based on the work carried out in validating the liner temperatures of a straight flow annular combustion chamber for an aero engine application. Limited experiments have been carried out by measuring the liner wall temperatures using k-type thermocouples along the liner axial length. The experiments on the combustion chamber testing are carried out at the engine level testing. The liner temperature which is numerically computed by CHT investigations using CFX code is verified with the experimental data. This helped in better understanding the flow characterization around and along the liner wall. The main flow variables used are the mass flow rate, temperature and the pressure at the combustor inlet. Initially, the fuel air ratio is used accordingly to maintain the same T4/T3 ratio. The effect of liner temperature with T3 is studied. Since T4 is constant, the liner temperature is only dependent on T3 and follows a specific temperature distribution for the given combustor geometry. Hence this approach will be very useful in estimating the liner temperatures at any given T3 for a given combustor geometry. Further the liner temperature is also estimated at other fuel air ratios (different T4/T3 ratios) by using the verified CHT numerical computations and found that TL/T3 remains almost constant for any air fuel ratio that is encountered in the operating envelope of the aero engine.
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Shouman, A. Radey, and A. R. Shouman. "The WISC Gas Turbine Engine." In ASME 1997 International Gas Turbine and Aeroengine Congress and Exhibition. American Society of Mechanical Engineers, 1997. http://dx.doi.org/10.1115/97-gt-493.

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Combined gas turbine-steam turbine cycles have gained widespread acceptance as the most efficient utilization of the gas turbine for power generation, particularly for large power plants. In order to maximize the achievable thermal efficiency, more than one exhaust heat recovery boiler is used. The current trend is to use three boilers at three different operating pressures, which improves thermal efficiency but significantly increases the initial cost of the plant. There are advantages in replacing an exhaust heat recovery system using multiple boilers by a single heat exchanger in which the water side pressure is above the critical pressure of water; we shall refer to such a heat exchanger as a supercritical heat exchanger. The supercritical steam leaving the heat exchanger is expanded in a two phase turbine and then fed into the engine combustor. A condenser and a water treatment system are used to recover most of the water in the exhaust stream. A turbine system identical to the basic engine turbine system is added in parallel in order to allow for the operation with increased mass flow due to the steam injection. To achieve maximum efficiency such a turbine should be provided with variable area nozzles. With this arrangement, it becomes possible to inject sufficient steam to produce stoichiometric combustion at the desired turbine inlet temperature. We shall refer to this cycle as the Water Injected Stoichiometric Combustion (WISC) gas turbine cycle. The various components described above can be added to any existing gas turbine engine to change it to the WISC configuration. The WISC engine offers significant economical advantages. The specific power output per pound of air for the WISC engine is more than five times that of the basic engine, the thermal efficiency is 75% higher than that of the basic engine. This produces a significant reduction in the initial investment in the plant as well as its operating expenses.
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Verma, Vishwas, Kiran Manoharan, and Jaydeep Basani. "Application of Machine Learning in Turbulent Combustion for Aviation Gas Turbine Combustor Design." In ASME 2021 Gas Turbine India Conference. American Society of Mechanical Engineers, 2021. http://dx.doi.org/10.1115/gtindia2021-76442.

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Abstract Numerical simulation of gas turbine combustors requires resolving a broad spectrum of length and time scales for accurate flow field and emission predictions. Reynold’s Averaged Navier Stokes (RANS) approach can generate solutions in few hours; however, it fails to produce accurate predictions for turbulent reacting flow field seen in general combustors. On the other hand, the Large Eddy Simulation (LES) approach can overcome this challenge, but it requires orders of magnitude higher computational cost. This limits designers to use the LES approach in combustor development cycles and prohibits them from using the same in numerical optimization. The current work tries to build an alternate approach using a data-driven method to generate fast and consistent results. In this work, deep learning (DL) dense neural network framework is used to improve the RANS solution accuracy using LES data as truth data. A supervised regression learning multilayer perceptron (MLP) neural network engine is developed. The machine learning (ML) engine developed in the present study can compute data with LES accuracy in 95% lesser computational time than performing LES simulations. The output of the ML engine shows good agreement with the trend of LES, which is entirely different from RANS, and to a reasonable extent, captures magnitudes of actual flow variables. However, it is recommended that the ML engine be trained using broad design space and physical laws along with a purely data-driven approach for better generalization.
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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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Reports on the topic "Gas Turbine Engine Combustion"

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Wong, J. K. L., G. N. Banks, and H. Whaley. Durability of gas turbine engine components in a bio-fuel combustion atmosphere. Natural Resources Canada/ESS/Scientific and Technical Publishing Services, 1995. http://dx.doi.org/10.4095/304635.

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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), April 2010. http://dx.doi.org/10.2172/1051563.

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Korjack, T. A. A Twisted Turbine Blade Analysis for a Gas Turbine Engine. Fort Belvoir, VA: Defense Technical Information Center, August 1997. http://dx.doi.org/10.21236/ada329581.

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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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Cao, Yiding. Miniature Heat Pipe Devices for Gas Turbine Engine Applications. Fort Belvoir, VA: Defense Technical Information Center, December 2002. http://dx.doi.org/10.21236/ada416715.

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Roth, P. G. Probabilistic Rotor Design System (PRDS) -- Gas Turbine Engine Design. Fort Belvoir, VA: Defense Technical Information Center, December 1998. http://dx.doi.org/10.21236/ada378908.

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