Relevant bibliographies by topics / Advanced gas turbine

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

Academic literature on the topic 'Advanced gas turbine'

Author: Grafiati
Published: 4 June 2021
Last updated: 13 February 2022

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Journal articles on the topic "Advanced gas turbine"

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TAKATA, Kazumasa, Keizo TSUKAGOSHI, Junichiro MASADA, and Eisaku ITO. "A102 DEVELOPMENT OF ADVANCED TECHNOLOGIES FOR THE NEXT GENERATION GAS TURBINE(Gas Turbine-1)." Proceedings of the International Conference on Power Engineering (ICOPE) 2009.1 (2009): _1–29_—_1–34_. http://dx.doi.org/10.1299/jsmeicope.2009.1._1-29_.

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Fukuizumi, Y., J. Masada, V. Kallianpur, and Y. Iwasaki. "Application of “H Gas Turbine” Design Technology to Increase Thermal Efficiency and Output Capability of the Mitsubishi M701G2 Gas Turbine." Journal of Engineering for Gas Turbines and Power 127, no. 2 (2005): 369–74. http://dx.doi.org/10.1115/1.1850490.

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Mitsubishi completed design development and verification load testing of a steam-cooled M501H gas turbine at a combined cycle power plant at Takasago, Japan in 2001. Several advanced technologies were specifically developed in addition to the steam-cooled components consisting of the combustor, turbine blades, vanes, and the rotor. Some of the other key technologies consisted of an advanced compressor with a pressure ratio of 25:1, active clearance control, and advanced seal technology. Prior to the M501H, Mitsubishi introduced cooling-steam in “G series” gas turbines in 1997 to cool combustor liners. Recently, some of the advanced design technologies from the M501H gas turbine were applied to the G series gas turbine resulting in significant improvement in output and thermal efficiency. A noteworthy aspect of the technology transfer is that the upgraded G series M701G2 gas turbine has an almost equivalent output and thermal efficiency as H class gas turbines while continuing to rely on conventional air cooling of turbine blades and vanes, and time-proven materials from industrial gas turbine experience. In this paper we describe the key design features of the M701G2 gas turbine that make this possible such as the advanced 21:1 compressor with 14 stages, an advanced premix DLN combustor, etc., as well as shop load test results that were completed in 2002 at Mitsubishi’s in-house facility.
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Almasi, A. "Advanced gas turbine packaging." Australian Journal of Mechanical Engineering 13, no. 1 (2015): 46–54. http://dx.doi.org/10.7158/m12-091.2015.13.1.

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Horlock, J. H., and William W. Bathie. "Advanced Gas Turbine Cycles." Journal of Engineering for Gas Turbines and Power 126, no. 4 (2004): 924. http://dx.doi.org/10.1115/1.1789994.

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Shibanuma, Tohru. "Advanced Aeroderivative Gas Turbine." JAPAN TAPPI JOURNAL 66, no. 6 (2012): 581–87. http://dx.doi.org/10.2524/jtappij.66.581.

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Eckardt, D., and P. Rufli. "Advanced Gas Turbine Technology: ABB/BCC Historical Firsts." Journal of Engineering for Gas Turbines and Power 124, no. 3 (2002): 542–49. http://dx.doi.org/10.1115/1.1470484.

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During more than 100 years engineers of the Swiss development center of A.-G. BBC Brown, Boveri & Cie., from 1988 onwards ABB Asea Brown Boveri Ltd., in 1999 ABB ALSTOM POWER Ltd., and now ALSTOM Power Ltd. in Baden, Switzerland, have significantly contributed to the achievement of today’s advanced gas turbine concept. Numerous “firsts” are highlighted in this paper—ranging from the first realization of the industrial, heavy-duty gas turbine in the 1930s to today’s high-technology gas turbine (GT) products, combining excellent performance, extraordinary low environmental impact with commercial attractiveness for global power generation. Interesting connections could be unveiled for the early parallel development of industrial and areo gas turbines.
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Maunsbach, K., A. Isaksson, J. Yan, G. Svedberg, and L. Eidensten. "Integration of Advanced Gas Turbines in Pulp and Paper Mills for Increased Power Generation." Journal of Engineering for Gas Turbines and Power 123, no. 4 (2001): 734–40. http://dx.doi.org/10.1115/1.1359773.

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The pulp and paper industry handles large amounts of energy and today produces the steam needed for the process and some of the required electricity. Several studies have shown that black liquor gasification and combined cycles increase the power production significantly compared to the traditional processes used today. It is of interest to investigate the performance when advanced gas turbines are integrated with next-generation pulp and paper mills. The present study focused on comparing the combined cycle with the integration of advanced gas turbines such as steam injected gas turbine (STIG) and evaporative gas turbine (EvGT) in pulp and paper mills. Two categories of simulations have been performed: (1) comparison of gasification of both black liquor and biomass connected to either a combined cycle or steam injected gas turbine with a heat recovery steam generator; (2) externally fired gas turbine in combination with the traditional recovery boiler. The energy demand of the pulp and paper mills is satisfied in all cases and the possibility to deliver a power surplus for external use is verified. The study investigates new system combinations of applications for advanced gas turbines.
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Bontempo, R., and M. Manna. "Efficiency optimisation of advanced gas turbine recuperative-cycles." Proceedings of the Institution of Mechanical Engineers, Part A: Journal of Power and Energy 234, no. 6 (2019): 817–35. http://dx.doi.org/10.1177/0957650919875909.

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The paper presents a theoretical analysis of three advanced gas turbine recuperative-cycles, that is, the intercooled, the reheat and the intercooled and reheat cycles. The internal irreversibilities, which characterise the compression and expansion processes, are taken into account through the polytropic efficiencies of the compressors and turbines. As customary in simplified analytical approaches, the study is carried out for an uncooled closed-circuit gas turbine without pressure losses in the heat exchangers and using a calorically perfect gas as working fluid. Although the accurate performance prediction of a real-gas turbine is prevented by these simplifying assumptions, this analysis provides a fast and simple approach which can be used to theoretically explain the main features of the three advanced cycles and to compare them highlighting pros and contra. The effect of the heat recuperation is investigated comparing the thermal efficiency of a given cycle type with those of two reference cycles, namely, the non-recuperative version of the analysed cycle and the simple cycle. As a result, the ranges of the intermediate pressure ratios returning a benefit in the thermal efficiency in comparison with the two reference cycles have been obtained for the first time. Finally, for the sole intercooled and reheat recuperative-cycle, a novel analytical expression for the intermediate pressure ratios yielding the maximum thermal efficiency is also given.
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Takeya, K., and H. Yasui. "Performance of the Integrated Gas and Steam Cycle (IGSC) for Reheat Gas Turbines." Journal of Engineering for Gas Turbines and Power 110, no. 2 (1988): 220–24. http://dx.doi.org/10.1115/1.3240107.

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In 1978, the Japanese government started a national project for energy conservation called the Moonlight Project. The Engineering Research Association for Advanced Gas Turbines was selected to research and develop an advanced gas turbine for this project. The development stages were planned as follows: first, the development of a reheat gas turbine for a pilot plant (AGTJ-100A), and second, a prototype plant (AGTJ-100B). The AGTJ-100A has been undergoing performance tests since 1984 at the Sodegaura Power Station of the Tokyo Electric Power Co., Inc. (TEPCO). The inlet gas temperature of the high-pressure turbine (HPT) of the AGTJ-100A is 1573 K, while that of the AGTJ-100B is 100 K higher. Therefore, various advanced technologies have to be applied to the AGTJ-100B HPT. Ceramic coating on the HPT blades is the most desirable of these technologies. In this paper, the present level of development, and future R & D plans for ceramic coating, are taken into consideration. Steam blade cooling is applied for the IGSC.
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Wright, W. E., and J. C. Hall. "Advanced Aircraft Gas Turbine Engine Controls." Journal of Engineering for Gas Turbines and Power 112, no. 4 (1990): 561–64. http://dx.doi.org/10.1115/1.2906205.

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With the advent of vectored thrust, vertical lift, and fly-by-wire aircraft, the complexity of aircraft gas turbine control systems has evolved to the point wherein they must approach or equal the reliability of current quad redundant flight control systems. To advance the technology of high-reliability engine controls, one solution to the Byzantine General’s problem (Lamport et al., 1982) is presented as the foundation for fault tolerant engine control architecture. In addition to creating a control architecture, an approach to managing the architecture’s redundancy is addressed.
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Dissertations / Theses on the topic "Advanced gas turbine"

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Pachidis, Vassilios. "Gas Turbine Advanced Performance Simulation." Thesis, Cranfield University, 2006. http://hdl.handle.net/1826/4529.

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Current commercial `state of the art' engine simulation software is of a low fidelity. Individual component performance characteristics are typically represented via nondimensional maps with empirical adjustments for off-design effects. Component nondimensional characteristics are usually obtained through the averaging of experimental readings from rig test analyses carried out under nominal operating conditions. In those cases where actual component characteristics are not available and default maps are used instead, conventional simulation tools can offer a good prediction of the performance of the whole engine close to design point, but can deviate substantially at of design and transient conditions. On the other hand, even when real component characteristics are available, zero-dimensional engine cycle simulation tools can not predict the performance of the engine at other than nominal conditions satisfactorily. Low-fidelity simulation tools are generally incapable of analyzing the performance of individual engine components in detail, or capturing complex physical phenomena such as inlet flow distortion. Although the available computational power has increased exponentially over the last two decades, a detailed, three-dimensional analysis of an entire propulsion system still seems to be so complex and computationally intensive as to remain cost-prohibitive. For this reason, alternative methods of integrating different types and levels of analysis are necessary. The integration of simulation codes that model at different levels of fidelity into a single simulation provides the opportunity to reduce the overall computing resource needed, while retaining the desired level of analysis in specific engine components. The objective of this work was to investigate different simulation strategies for communicating the performance characteristics of an isolated gas turbine engine component, resolved from a detailed, high-fidelity analysis, to an engine system analysis carried out at a lower level of resolution. This would allow component-level, complex physical processes to be captured and analyzed in the context of the whole engine performance, at an affordable computing resource and time. More specifically, this work identified and thoroughly investigated several advanced simulation strategies in terms of their actual implementation and potential, by looking into relative changes in engine performance after integrating into the basic, nondimensional cycle analysis, the performance characteristics of i) two-dimensional Streamline Curvature (SLC) and ii) three-dimensional Computational Fluid Dynamics (CFD), engine component models. In the context of this work, several case studies were carried out, utilising different two-dimensional and three-dimensional component geometries, under different operating conditions, such as different types and extents of compressor inlet pressure distortion and turbine inlet temperature distortion. More importantly, this research effort established the necessary methodology and technology required for a full, twodimensional engine cycle analysis at an affordable computational resource.
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Pachidis, Vassilios A. "Gas turbine advanced performance simulation." Thesis, Cranfield University, 2006. http://dspace.lib.cranfield.ac.uk/handle/1826/4529.

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Current commercial 'state of the art' engine simulation software is of a low fidelity. Individual component performance characteristics are typically represented via nondimensional maps with empirical adjustments for off-design effects. Component nondimensional characteristics are usually obtained through the averaging of experimental readings from rig test analyses carried out under nominal operating conditions. In those cases where actual component characteristics are not available and default maps are used instead, conventional simulation tools can offer a good prediction of the performance of the whole engine close to design point, but can deviate substantially at of design and transient conditions. On the other hand, even when real component characteristics are available, zero-dimensional engine cycle simulation tools can not predict the performance of the engine at other than nominal conditions satisfactorily. Low-fidelity simulation tools are generally incapable of analyzing the performance of individual engine components in detail, or capturing complex physical phenomena such as inlet flow distortion. Although the available computational power has increased exponentially over the last two decades, a detailed, three-dimensional analysis of an entire propulsion system still seems to be so complex and computationally intensive as to remain cost-prohibitive. For this reason, alternative methods of integrating different types and levels of analysis are necessary. The integration of simulation codes that model at different levels of fidelity into a single simulation provides the opportunity to reduce the overall computing resource needed, while retaining the desired level of analysis in specific engine components. The objective of this work was to investigate different simulation strategies for communicating the performance characteristics of an isolated gas turbine engine component, resolved from a detailed, high-fidelity analysis, to an engine system analysis carried out at a lower level of resolution. This would allow component-level, complex physical processes to be captured and analyzed in the context of the whole engine performance, at an affordable computing resource and time. More specifically, this work identified and thoroughly investigated several advanced simulation strategies in terms of their actual implementation and potential, by looking into relative changes in engine performance after integrating into the basic, nondimensional cycle analysis, the performance characteristics of i) two-dimensional Streamline Curvature (SLC) and ii) three-dimensional Computational Fluid Dynamics (CFD), engine component models. In the context of this work, several case studies were carried out, utilising different two-dimensional and three-dimensional component geometries, under different operating conditions, such as different types and extents of compressor inlet pressure distortion and turbine inlet temperature distortion. More importantly, this research effort established the necessary methodology and technology required for a full, twodimensional engine cycle analysis at an affordable computational resource.
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Bartlett, Michael. "Developing Humidified Gas Turbine Cycles." Doctoral thesis, KTH, Chemical Engineering and Technology, 2002. http://urn.kb.se/resolve?urn=urn:nbn:se:kth:diva-3437.

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As a result of their unique heat recovery properties,Humidified Gas Turbine (HGT) cycles have the potential todeliver resource-effective energy to society. The EvaporativeGas Turbine (EvGT) Consortium in Sweden has been studying thesetypes of cycles for nearly a decade, but now stands at acrossroads, with commercial demonstration remaining. Thisthesis binds together several key elements for the developmentof humidified gas turbines: water recovery and air and waterquality in the cycle, cycle selection for near-term, mid-sizedpower generation, and identifying a feasible niche market fordemonstration and market penetration. Moreover, possiblesocio-technical hinders for humidified gas turbine developmentare examined.

Through modelling saltcontaminant flows in the cycle andverifying the results in the pilot plant, it was found thathumidification tower operation need not endanger the hot gaspath. Moreover, sufficient condensate can be condensed to meetfeed water demands. Air filters were found to be essential tolower the base level of contaminant in the cycle. This protectsboth the air and water stream components. By capturing airparticles of a similar size to the air filters, the humidifieractually lowers air stream salt levels. Measures to minimisedroplet entrainment were successful (50 mg droplets/kg air) andmodels predict a 1% blow down from the water circuit issufficient. The condensate is very clean, with less than 1 mg/lalkali salts and easily deionised.

Based on a core engine parameter analysis for three HGTcycle configurations and a subsequent economic study, asteam-cooled steam injected cycle complemented with part-flowhumidification is recommended for the mid-size power market.This cycle was found to be particularly efficient at highpressures and turbine inlet temperatures, conditions eased bysteam cooling and even intercooling. The recommended HGT cyclegives specific investment costs 30- 35% lower than the combinedcycles and cost of electricity levels were 10-18% lower.Full-flow intercooled EvGT cycles give high performances, butseem to be penalised by the recuperator costs, while stillbeing cheaper than the CC. District heating is suggested as asuitable niche market to commercially demonstrate the HGTcycle. Here, the advantages of HGT are especially pronounceddue their very high total efficiencies. Feasibility prices forelectricity were up to 35% lower than competing combinedcycles. HGT cycles were also found to effectively include wasteheat sources.

Keywords:gas turbines, evaporative gas turbines,humidification, power generation, combined heat and powergeneration.

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Langmaak, Stephan. "Cost optimization tools for advanced gas turbine technologies." Thesis, University of Southampton, 2015. https://eprints.soton.ac.uk/388048/.

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This thesis presents two studies that illustrate how cost modelling can be integrated into the various design process stages, ranging from strategic gas turbine and airframe system design to preliminary and detailed component design and production planning. The first study investigates which cruise speed the next generation of short-haul aircraft with 150 seats should fly at and whether a conventional two- or three-shaft turbofan, a geared turbofan, a turboprop or an open rotor should be employed in order to make the aircraft's direct operating cost robust to uncertain fuel and carbon (CO2) prices in the Year 2030, taking the aircraft productivity, the passenger value of time and the modal shift into account. To answer this question, an optimization loop was set up in MATLAB consisting of nine modules covering gas turbine and airframe design and performance, light and aircraft fleet simulation, operating cost and optimization. If the passenger value of time is included, the most robust aircraft design is powered by geared turbofan engines and cruises at Mach 0.80. If the value of time is ignored, however, then a turboprop aircraft flying at Mach 0.70 is the optimum solution. This demonstrates that the most fuel-efficient option, the open rotor, is not automatically the most cost-efficient solution because of the relatively high engine and airframe costs. The second study shows how a factory cost model can be combined with a parametric component production time model, to not only calculate costs at the manufacturing operation level for production planning, but also the total unit costs of future integrally bladed disc (blisk) designs for component trade-off studies. As future process times can only be estimated and the correlation between operation times and blisk design parameters, including the number of blades, the disc diameter and other design variables, is never perfect, all operation times have uncertainty distributions. These are cascaded through the model to generate a probability distribution of the unit cost.
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Adams, Juan Carlos. "Advanced heat transfer surfaces for gas turbine heat exchangers." Thesis, University of Oxford, 2004. http://ethos.bl.uk/OrderDetails.do?uin=uk.bl.ethos.534221.

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Kersten, Stephanie. "Cooling techniques for advanced gas turbines." Honors in the Major Thesis, University of Central Florida, 2008. http://digital.library.ucf.edu/cdm/ref/collection/ETH/id/1097.

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This item is only available in print in the UCF Libraries. If this is your Honors Thesis, you can help us make it available online for use by researchers around the world by following the instructions on the distribution consent form at http://library.ucf.edu/Systems/DigitalInitiatives/DigitalCollections/InternetDistributionConsentAgreementForm.pdf You may also contact the project coordinator, Kerri Bottorff, at kerri.bottorff@ucf.edu for more information.
Bachelors
Engineering and Computer Science
Aerospace Engineering
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Roy-Aikins, J. E. A. "A study of variable geometry in advanced gas turbines." Thesis, Cranfield University, 1988. http://hdl.handle.net/1826/3907.

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The loss of performance of a gas turbine engine at off-design is primarily due to the rapid drop of the major cycle performance parameters with decrease in power and this may be aggravated by poor component performance. More and more stringent requirements are being put on the performance demanded from gas turbines and if future engines are to exhibit performances superior to those of present day: engines, then a means must be found of controlling engine cycle such that the lapse rate of the major cycle parameters with power is reduced. In certain applications, it may be desirable to vary engine cycle with operating conditions in an attempt to re-optimize performance. Variable geometry in key engine components offers the advantage of either improving the internal performance of a component or re-matching engine cycle to alter the flow-temperature-pressure relationships. Either method has the potential to improve engine performance. Future gas turbines, more so those for aeronautical applications, will extensively use variable geometry components and therefore, a tool must exist which is capable of evaluating the off-design performance of such engines right from the conceptual stage. With this in mind, a computer program was developed which can simulate the steady state performance of arbitrary gas turbines with or without variable geometry in the gas path components. The program is a thermodynamic component-matching analysis program which uses component performance maps to evaluate the conditions of the gas at the various engine stations. The program was used to study the performance of a number of cycles incorporating variable geometry and it was concluded that variable geometry can significantly improve the off-design performance of gas turbines.
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Metz, Stephen D. "Real time Marine Gas Turbine simulation for advanced controller design." Thesis, Monterey, California. Naval Postgraduate School, 1989. http://hdl.handle.net/10945/26202.

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Sethi, Vishal. "Advanced performance simulation of gas turbine components and fluid thermodynamic properties." Thesis, Cranfield University, 2008. http://dspace.lib.cranfield.ac.uk/handle/1826/5654.

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The VIVACE European Cycle Program (“VIVACE-ECP”) was part of the virtual engine sub-project of VIVACE and was worth 6.63 million Euros. The main outcome of the “VIVACE-ECP” was the development of a cost effective gas turbine simulation environment called PROOSIS. PROOSIS, which is the Greek word for “propulsion”, is an acronym for “PRopulsion Object Oriented SImulation Software”. PROOSIS was developed by facilitating optimal use of multi-partner gas turbine performance simulation research and development resources and expertise. PROOSIS is a single framework which provides shared standards and methodologies for the European Union (EU) gas turbine community, including original equipment manufacturers (OEMs), industrial companies, universities and research centres. The primary objective of this doctoral thesis is to present advanced performance simulation models of gas turbine components and advanced fluid modelling capabilities developed by the author for the PROOSIS standard components library (SCLib). The main aims of this research are to provide a detailed insight into the effects of dissociation on fluid thermodynamic properties and subsequently on gas turbine performance. Detailed descriptions of the development of an advanced fluid model and a robust flow continuity model, which are the foundation of the PROOSIS standard component library, are provided. The effects of dissociation on isolated Burner and Afterburner components as well as overall engine performance are discussed with the aid of several case studies. Additionally, advanced performance simulation models of Burner and Afterburner components are presented. The development of an extended parametric representation of compressor characteristics is also analysed. Several advanced capabilities of PROOSIS (including test analysis, customer deck generation, 3D compressor zooming and distributed computing) are also introduced. The “evolution of PROOSIS” is presented with an in-depth analysis of the collaborative structure and project management of the VIVACE- ECP, as well as the channels of communication, technology transfer and quality control. A clear emphasis is placed on the contribution of the author to each of these tasks and subsequently the “VIVACE-ECP” as a whole. The main outcome of this work is the development of an advanced fluid model which comprises multi-dimensional fluid property tables for several fuels. The advanced fluid model also caters for “levels of dissociation” ranging from “no dissociation” to chemical equilibrium. This advanced fluid model is complimented by a robust flow continuity model, also developed by the author, which calculates the unknown local flow properties at any point in an engine model. These robust, advanced fluid and flow continuity models facilitate improved accuracy thereby providing a solid foundation for several advanced gas turbine performance simulation capabilities.
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Sampath, Suresh. "Fault diagnostics for advanced cycle marine gas turbine using genetic algorithm." Thesis, Cranfield University, 2003. http://dspace.lib.cranfield.ac.uk/handle/1826/10204.

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The major challenges faced by the gas turbine industry, for both the users and the manufacturers, is the reduction in life cycle costs , as well as the safe and efficient running of gas turbines. In view of the above, it would be advantageous to have a diagnostics system capable of reliably detecting component faults (even though limited to gas path components) in a quantitative marmer. V This thesis presents the development an integrated fault diagnostics model for identifying shifts in component performance and sensor faults using advanced concepts in genetic algorithm. The diagnostics model operates in three distinct stages. The rst stage uses response surfaces for computing objective functions to increase the exploration potential of the search space while easing the computational burden. The second stage uses the heuristics modification of genetics algorithm parameters through a master-slave type configuration. The third stage uses the elitist model concept in genetic algorithm to preserve the accuracy of the solution in the face of randomness. The above fault diagnostics model has been integrated with a nested neural network to form a hybrid diagnostics model. The nested neural network is employed as a pre- processor or lter to reduce the number of fault classes to be explored by the genetic algorithm based diagnostics model. The hybrid model improves the accuracy, reliability and consistency of the results obtained. In addition signicant improvements in the total run time have also been observed. The advanced cycle Intercooled Recuperated WR2l engine has been used as the test engine for implementing the diagnostics model.
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Books on the topic "Advanced gas turbine"

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Advanced gas turbine cycles. [Pergamon], 2003.

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

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Janicka, Johannes. Flow and Combustion in Advanced Gas Turbine Combustors. Springer Netherlands, 2013.

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Janicka, Johannes, Amsini Sadiki, Michael Schäfer, and Christof Heeger, eds. Flow and Combustion in Advanced Gas Turbine Combustors. Springer Netherlands, 2013. http://dx.doi.org/10.1007/978-94-007-5320-4.

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The Impact of advanced materials on small turbine engines. Society of Automotive Engineers, 1991.

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Metz, Stephen D. Real time Marine Gas Turbine simulation for advanced controller design. Naval Postgraduate School, 1989.

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Hanley, David. Advanced high temperature polymer matrix composites for gas turbine engines program expansion. National Aeronautics and Space Administration, Glenn Research Center, 1999.

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Maccagno, T. M. Processing of advanced ceramics which have potential for use in gas turbine aero engines. National Research Council Canada, 1989.

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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. National Aeronautics and Space Administration, 1990.

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Pilz, S. A. H. Optimisation of advanced gas-turbine-based cycles for power generation, using pinch technology and exergy analysis. UMIST, 1994.

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Book chapters on the topic "Advanced gas turbine"

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Gicquel, Renaud. "Advanced gas turbine cycles." In Energy Systems, 2nd ed. CRC Press, 2021. http://dx.doi.org/10.1201/9781003175629-18.

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Akimoto, Hajime, Yoshinari Anoda, Kazuyuki Takase, Hiroyuki Yoshida, and Hidesada Tamai. "Gas Turbine Cycles and Steam Cycles." In An Advanced Course in Nuclear Engineering. Springer Japan, 2016. http://dx.doi.org/10.1007/978-4-431-55603-9_4.

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Garcia-Revillo, Francisco Javier, Jesús R. Jimenez-Octavio, Cristina Sanchez-Rebollo, and Alexis Cantizano. "Efficient Multi-objective Optimization for Gas Turbine Discs." In Advanced Structured Materials. Springer International Publishing, 2014. http://dx.doi.org/10.1007/978-3-319-07383-5_17.

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Härkegård, G. "The Design Needs for Advanced Gas Turbine Blading." In Materials for Advanced Power Engineering 1994. Springer Netherlands, 1994. http://dx.doi.org/10.1007/978-94-011-1048-8_53.

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Kevin, Rivera, Ricci Matt, and Gregory Otto. "Advanced Sensors for CMC Gas Turbine Engine Components." In Proceeding of the 42nd International Conference on Advanced Ceramics and Composites. John Wiley & Sons, Inc., 2019. http://dx.doi.org/10.1002/9781119543381.ch13.

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Böhm, B., D. Geyer, M. A. Gregor, et al. "Advanced Laser Diagnostics for Understanding Turbulent Combustion and Model Validation." In Flow and Combustion in Advanced Gas Turbine Combustors. Springer Netherlands, 2012. http://dx.doi.org/10.1007/978-94-007-5320-4_4.

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Kim, Hyung Ick, Hong Sun Park, Bong Kook Bae, Young Min Lee, Chang Sung Seok, and Moon Young Kim. "Evaluation of High Temperature Characteristics in Gas Turbine Blades." In Advanced Nondestructive Evaluation I. Trans Tech Publications Ltd., 2006. http://dx.doi.org/10.4028/0-87849-412-x.632.

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Hancock, P., and M. Malik. "Coating Systems and Technologies for Gas Turbine Applications." In Materials for Advanced Power Engineering 1994. Springer Netherlands, 1994. http://dx.doi.org/10.1007/978-94-011-1048-8_57.

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Wood, M. I. "Condition Assessment of Ex-Service Gas Turbine Blading." In Materials for Advanced Power Engineering 1994. Springer Netherlands, 1994. http://dx.doi.org/10.1007/978-94-011-1048-8_74.

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Opfer, L., I. V. Roisman, and C. Tropea. "Primary Atomization in an Airblast Gas Turbine Atomizer." In Flow and Combustion in Advanced Gas Turbine Combustors. Springer Netherlands, 2012. http://dx.doi.org/10.1007/978-94-007-5320-4_1.

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Conference papers on the topic "Advanced gas turbine"

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Matsuzaki, H., Y. Suto, Y. Kanazawa, M. Sato, I. Kobayashi, and Y. Kobayashi. "Development of Advanced Gas Turbine." In ASME 1996 International Gas Turbine and Aeroengine Congress and Exhibition. American Society of Mechanical Engineers, 1996. http://dx.doi.org/10.1115/96-gt-294.

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There is a strong demand for efficient and clean power generation systems which can cope with the energy shortage and the global environmental problems. As one of the measures to meet this demand, Tohoku Electric Power Company, in cooperation with the three domestic gas turbine manufacturers, has been developing since 1989 the key technologies for the next generation high efficiency gas turbine of a 1,500°C class of firing temperature. The aim is to achieve over 55% (LHV) thermal efficiency in a LNG comhined cycle power plant. In this research, Tohoku Electric Power Company have developed: (1) advanced cooling schemes for 1st stage vanes and blades, (2) heat resistant materials for 1st stage vanes and blades and (3) high temperature low NOx combustor, which are the key technologies required for realizing a 1,500 °C class high efficiency gas turbine with a potential for practical use.
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Holmes, James E., Howard F. Creveling, and Charles E. Horton. "Advanced Coal-Fueled Gas Turbine." In 1988 Conference and Exposition on Future Transportation Technology. SAE International, 1988. http://dx.doi.org/10.4271/881160.

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Sato, T., S. Aoki, and H. Mori. "A Gas Turbine Interactive Design System — TDSYS — for Advanced Gas Turbines." In 1985 Joint Power Generation Conference: GT Papers. American Society of Mechanical Engineers, 1985. http://dx.doi.org/10.1115/85-jpgc-gt-11.

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The characteristics and experiences of the gas turbine interactive design system, TDSYS, are described. The design of high performance advanced gas turbines requires complex trade-off analyses for optimization and hence it is necessary to use a highly efficient and accurate computerised integrated design system to complete the laborious design jobs in a short time. TDSYS is an interactive design system which makes extensive use of computer graphics and enables the designers to complete a gas turbine blade design systematically in a very short time. TDSYS has been developed and continuously improved over a period of ten years. The system has been used for the complete and retrofit design of many gas turbines including Mitsubishi MW701 and AGTJ-100A which is a high efficiency reheat gas turbine now being developed under a Japanese national project. In this paper, typical design samples of high temperature turbines are also presented.
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Boyd, G. L., J. R. Kidwell, and D. M. Kreiner. "AGT101 Advanced Gas Turbine Technology Update." In ASME 1986 International Gas Turbine Conference and Exhibit. American Society of Mechanical Engineers, 1986. http://dx.doi.org/10.1115/86-gt-305.

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The Garrett/Ford Advanced Gas Turbine Technology Development Program, designated AGT101, has made significant progress during 1985 encompassing ceramic engine and ceramic component testing. Engine testing has included full speed operation to 100,000 rpm and 1149C (2100F) turbine inlet temperature, initial baseline performance mapping and ceramic combustor start and steady state operation. Over 380 hours of test time have been accumulated on four development engines. High temperature foil bearing coatings have passed rig test and a thick precious metal foil coating selected for engine evaluation. Ceramic structures have been successfully rig tested at 1371C (2500F) for over 27 hours. Interface compatibility testing conducted during these runs indicate RBSN-to-RBSN or SASC-to-SASC result in “sticking” — however, RBSN-to-SASC in either planar or line contact show no evidence of sticking. Ceramic combustor rig tests have demonstrated acceptable lightoffs using either a conventional ignitor or a commercially available glow plug. Operation to 1371C (2500F) combustor discharge temperatures have also been demonstrated. Ceramic turbine rotor fabrication efforts have continued at ACC and Ford. Kyocera and NGK-Locke also have been working on the rotor. Several rotors have been received and are currently undergoing final machining and qualification tests. Testing of the all-ceramic AGT101 engine is currently scheduled for late 1985.
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Anton, Reiner, Brigitte Heinecke, Michael Ott, and Rolf Wilkenhoener. "Repair of Advanced Gas Turbine Blades." In ASME Turbo Expo 2007: Power for Land, Sea, and Air. ASMEDC, 2007. http://dx.doi.org/10.1115/gt2007-28208.

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The availability and reliability of gas turbine units are critical for success to gas turbine users. Advanced hot gas path components that are used in state-of-the-art gas turbines have to ensure high efficiency, but require advanced technologies for assessment during maintenance inspections in order to decide whether they should be reused or replaced. Furthermore, advanced repair and refurbishment technologies are vital due to the complex nature of such components (e.g., Directionally Solidified (DS) / Single Crystal (SC) materials, thin wall components, new cooling techniques). Advanced repair technologies are essential to allow cost effective refurbishing while maintaining high reliability, to ensure minimum life cycle cost. This paper will discuss some aspects of Siemens development and implementation of advanced technologies for repair and refurbishment. In particular, the following technologies used by Siemens will be addressed: • Weld restoration; • Braze restoration processes; • Coating; • Re-opening of cooling holes.
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Bancalari, Ed, Pedy Chan, and Ihor S. Diakunchak. "Advanced Hydrogen Gas Turbine Development Program." In ASME Turbo Expo 2007: Power for Land, Sea, and Air. ASMEDC, 2007. http://dx.doi.org/10.1115/gt2007-27869.

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The U.S. Department of Energy (DOE) has awarded Siemens Power Generation the first two phases for the Advanced Hydrogen Turbine Development Program. The 3-phase, multi-year program goals are to develop an advanced syngas, hydrogen and natural gas fired gas turbine fully integrated into coal-based Integrated Gasification Combined Cycle (IGCC) plants. The Program objectives are to demonstrate 3–5 percentage points efficiency improvement over current state of the art, less than 2 ppm NOx @ 15% O2 and reduction in plant capital cost. An additional objective is to show how the advanced gas turbine – IGCC plant can be configured for CO2 sequestration readiness. These objectives represent the overall DOE Advanced Power System goal to conduct Research and Development necessary to produce fuel flexible, CO2 sequestration ready advanced IGCC power systems for FutureGen type applications. Phase 1 entails advanced technologies identification, research and development Implementation Plan preparation and new gas turbine component conceptual designs. Phase 2 focuses on novel technologies development, validation, down selection and advanced gas turbine detail design. Phase 3 involves advanced gas turbine and IGCC plant construction and validation testing to demonstrate that efficiency, emissions and cost goals will be achieved and to prove the system’s commercial viability. The end objective is to validate the advanced gas turbine technology by 2015. The SGT6-6000G was selected as the basis for this development effort, due to its high firing temperature, output power and efficiency, as well as its advanced secondary air and steam cooling systems. It will be adapted for operation on coal, refinery residue and biomass derived hydrogen and syngas fuels, as well as natural gas, while achieving high performance levels and reduced plant capital costs in $/kW. New or enhanced technologies required to achieve high plant efficiency, while minimizing emissions and capital cost, will be developed and gas turbine design changes needed for optimum integration into the IGCC plant will be carried out. The main development thrust will be in the combustion, turbine cooling, materials/coating technologies and engine integration/operational flexibility. Several combustion systems will be investigated and the most successful candidate down selected. To minimize cooling air consumption, novel cooling concepts will be investigated, and validated in rig tests. Advanced bond coats, thermal barrier coatings, superalloys and airfoil architectures will be developed to minimize cooling air use. This paper describes the first year’s Phase 1 activities in advanced concepts, technologies identification and development, plant thermal performance evaluation, gas turbine IGCC plant integration studies and new gas turbine component conceptual designs.
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McGraw, Julie, Reiner Anton, Christian Ba¨hr, and Mary Chiozza. "Repair of Advanced Gas Turbine Blades." In ASME 2005 Power Conference. ASMEDC, 2005. http://dx.doi.org/10.1115/pwr2005-50229.

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In order to promote high efficiency combined with high power output, reliability, and availability, Siemens advanced gas turbines are equipped with state-of-the-art turbine blades and hot gas path parts. These parts embody the latest developments in base materials (single crystal and directionally solidified), as well as complex cooling arrangements (round and shaped holes) and coating systems. A modern gas turbine blade (or other hot gas path part) is a duplex component consisting of base material and coating system. Planned recoating and repair intervals are established as part of the blade design. Advanced repair technologies are essential to allow cost-effective refurbishing while maintaining high reliability. This paper gives an overview of the operating experience and key technologies used to repair these parts.
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Burkhardt, Simon. "Advanced Gas Turbine Combustor Cooling Configurations." In International Symposium on Heat Transfer in Turbomachinery. Begellhouse, 1994. http://dx.doi.org/10.1615/ichmt.1994.intsymphetattransturb.200.

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9

Kidwell, J. R., and D. M. Kreiner. "AGT 101: Advanced Gas Turbine Technology Update." In ASME 1985 International Gas Turbine Conference and Exhibit. American Society of Mechanical Engineers, 1985. http://dx.doi.org/10.1115/85-gt-177.

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The Garrett/Ford AGT101 program has made significant progress during 1984 in ceramic component and engine test bed development, including initial ceramic engine testing. All ceramic components for the AGT101 [1644K (2500F)] engine are now undergoing development. Ceramic structures have been undergoing extensive analysis, design modification, and rig testing. AGT101 [1644K (2500F)] start capability has been demonstrated in rig tests. Also, 1644K (2500F) steady-state testing has been initiated in the test rigs to obtain a better understanding of ceramics in that environment. The ceramic turbine rotor has progressed through cold spin test 12,040 rad/sec (115,000 rpm) and hot turbine rig test, and is currently in initial phases of engine test. Over 400 hours of engine testing is expected by March, 1985, including approximately 150 hours of operation and 50 starts on the 1422K (2100F) engine. All activities are progressing toward 1644K (2500F) engine testing in mid 1985.
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Beitel, Gregg, David Plemmons, Daniel Catalano, and Kent Wilcher. "Advanced Embedded Instrumentation for Gas Turbine Engines." In 2008 U.S. Air Force T&E Days. American Institute of Aeronautics and Astronautics, 2008. http://dx.doi.org/10.2514/6.2008-1675.

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Reports on the topic "Advanced gas turbine"

1

Unknown. ADVANCED GAS TURBINE SYSTEMS RESEARCH. Office of Scientific and Technical Information (OSTI), 2002. http://dx.doi.org/10.2172/791987.

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Unknown. ADVANCED GAS TURBINE SYSTEMS RESEARCH. Office of Scientific and Technical Information (OSTI), 2002. http://dx.doi.org/10.2172/793004.

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Unknown. ADVANCED GAS TURBINE SYSTEMS RESEARCH. Office of Scientific and Technical Information (OSTI), 2002. http://dx.doi.org/10.2172/794939.

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Unknown. ADVANCED GAS TURBINE SYSTEMS RESEARCH. Office of Scientific and Technical Information (OSTI), 1999. http://dx.doi.org/10.2172/769312.

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Unknown. ADVANCED GAS TURBINE SYSTEMS RESEARCH. Office of Scientific and Technical Information (OSTI), 1999. http://dx.doi.org/10.2172/769313.

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Unknown. ADVANCED GAS TURBINE SYSTEMS RESEARCH. Office of Scientific and Technical Information (OSTI), 2000. http://dx.doi.org/10.2172/766242.

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7

Horner, M. W., E. E. Ekstedt, E. Gal, et al. Advanced Coal-Fueled Gas Turbine Program. Office of Scientific and Technical Information (OSTI), 1989. http://dx.doi.org/10.2172/5562924.

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York, William, Michael Hughes, Jonathan Berry, et al. Advanced IGCC/Hydrogen Gas Turbine Development. Office of Scientific and Technical Information (OSTI), 2015. http://dx.doi.org/10.2172/1261809.

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9

Wenglarz, R. A. Advanced coal-fueled gas turbine systems. Office of Scientific and Technical Information (OSTI), 1994. http://dx.doi.org/10.2172/10193506.

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Lawrence P. Golan. ADVANCED GAS TURBINE SYSTEMS RESEARCH PROGRAM. Office of Scientific and Technical Information (OSTI), 2000. http://dx.doi.org/10.2172/824019.

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