Relevant bibliographies by topics / Turbine a gas

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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 'Turbine a gas'

Author: Grafiati
Published: 4 June 2021
Last updated: 10 March 2023

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Journal articles on the topic "Turbine a gas"

1

Valenti, Michael. "Keeping it Cool." Mechanical Engineering 123, no. 08 (August 1, 2001): 48–52. http://dx.doi.org/10.1115/1.2001-aug-2.

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This article provides details of various aspects of air cooling technologies that can give gas turbines a boost. Air inlet cooling raises gas turbine efficiency, which is proportional to the mass flow of air fed into the turbine. The higher the mass flow, the greater the amount of electricity produced from the gas burned. Researchers at Mee Industries conduct laser scattering studies of their company’s fogging nozzles to determine if the nozzles project properly sized droplets for cooling. The goal for turbine air cooling systems is to reduce the temperature of inlet air from the dry bulb temperature, the ambient temperature, to the wet bulb temperature. The Turbidek evaporative cooling system designed by Munters Corp. of Fort Myers, Florida, is often retrofit to turbines, typically installed in front of pre-filters that remove particulates from inlet air. Turbine Air Systems designs standard chillers to improve the performance of the General Electric LM6000 and F-class gas turbines during the hottest weather.
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AOKI, Shigeki, Kiyoshi MATSUMOTO, Yasushi DOUURA, Takeo ODA, Masahiro Ogata, and Yasuhiro KINOSHITA. "A106 Upgraded lineup of KAWASAKI Green Gas Turbine combustion systems(Gas Turbine-2)." Proceedings of the International Conference on Power Engineering (ICOPE) 2009.1 (2009): _1–53_—_1–57_. http://dx.doi.org/10.1299/jsmeicope.2009.1._1-53_.

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Bander, F. "Multifuel Gas Turbine Propulsion for Naval Ships: Gas Turbine Cycles Implementing a Rotating Gasifier." Journal of Engineering for Gas Turbines and Power 107, no. 3 (July 1, 1985): 758–68. http://dx.doi.org/10.1115/1.3239798.

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The purpose of this paper is to investigate the possibilities of implementing a rotating gasifier to convert aero-derived gas turbines into multifuel ship propulsion units, thereby combining the advantages of lightweight and compact gas turbines with the multifuel characteristics of a rotating gasifier. Problems (and possible solutions) to be discussed are: (i) aerodynamic interaction between gas turbine and gasifier; (ii) attaining maximum energy productivity together with ease of control; (iii) corrosion and/or erosion of gas turbine components.
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Brady, C. O., and D. L. Luck. "The Increased Use of Gas Turbines as Commercial Marine Engines." Journal of Engineering for Gas Turbines and Power 116, no. 2 (April 1, 1994): 428–33. http://dx.doi.org/10.1115/1.2906839.

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Over the last three decades, aeroderivative gas turbines have become established naval ship propulsion engines, but use in the commercial marine field has been more limited. Today, aeroderivative gas turbines are being increasingly utilized as commercial marine engines. The primary reason for the increased use of gas turbines is discussed and several recent GE aeroderivative gas turbine commercial marine applications are described with particular aspects of the gas turbine engine installations detailed. Finally, the potential for future commercial marine aeroderivative gas turbine applications is presented.
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Sanaye, Sepehr, and Salahadin Hosseini. "Off-design performance improvement of twin-shaft gas turbine by variable geometry turbine and compressor besides fuel control." Proceedings of the Institution of Mechanical Engineers, Part A: Journal of Power and Energy 234, no. 7 (December 3, 2019): 957–80. http://dx.doi.org/10.1177/0957650919887888.

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A novel procedure for finding the optimum values of design parameters of industrial twin-shaft gas turbines at various ambient temperatures is presented here. This paper focuses on being off design due to various ambient temperatures. The gas turbine modeling is performed by applying compressor and turbine characteristic maps and using thermodynamic matching method. The gas turbine power output is selected as an objective function in optimization procedure with genetic algorithm. Design parameters are compressor inlet guide vane angle, turbine exit temperature, and power turbine inlet nozzle guide vane angle. The novel constrains in optimization are compressor surge margin and turbine blade life cycle. A trained neural network is used for life cycle estimation of high pressure (gas generator) turbine blades. Results for optimum values for nozzle guide vane/inlet guide vane (23°/27°–27°/6°) in ambient temperature range of 25–45 ℃ provided higher net power output (3–4.3%) and more secured compressor surge margin in comparison with that for gas turbines control by turbine exit temperature. Gas turbines thermal efficiency also increased from 0.09 to 0.34% (while the gas generator turbine first rotor blade creep life cycle was kept almost constant about 40,000 h). Meanwhile, the averaged values for turbine exit temperature/turbine inlet temperature changed from 831.2/1475 to 823/1471°K, respectively, which shows about 1% decrease in turbine exit temperature and 0.3% decrease in turbine inlet temperature.
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Gregory, Brent A. "How Many Turbine Stages?" Mechanical Engineering 139, no. 05 (May 1, 2017): 56–57. http://dx.doi.org/10.1115/1.2017-may-5.

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This article discusses various stages of turbines and the importance of having more stages in turbine design. The article also highlights reasons that determine the designer’s choice to select the number of turbine stages for a given design of gas turbine. The highest performance turbines are defined by lower work requirements and slower velocities in the gas path. The fundamental factors determining performance might be relegated to only two factors: demand on the turbine and axial velocity. Aircraft engine technologies drive new initiatives because of the need to increase firing temperature and dramatically improve efficiency for substantially less weight. Also, the expansion across each stage determined the annulus area so that the optimums implied by the Pearson chart were largely ignored in the article. Developments in aircraft engine gas turbines have forced heavy frame gas turbines’ original equipment manufacturers to rethink many historical paradigms.
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Karusitio Silaban, Haleonar Mycson, and Abdul Ghofur. "ANALISA PERFORMA TURBIN GAS TIPE CW251 B11 PADA SYSTEM PEMBANGKITAN LISTRIK TENAGA GAS SEKTOR PEMBANGKITAN BALI." JTAM ROTARY 2, no. 2 (September 29, 2020): 161. http://dx.doi.org/10.20527/jtam_rotary.v2i2.2412.

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Di Bali, kebutuhan listrik berdasarkan data PLN 446.172 MW. Untuk memenuhi kebutuhan beban ini, PLN Bali mengandalkan empat pembangkit listrik berbeda di Pesanggaran, Gilimanuk, Pemaron, dan Pontianak. Sebagian besar pembangkit listrik di Bali menggunakan Pembangkit Listrik Tenaga Gas. Pada pembangkit gas generasi Bali terjadi kerusakan pada bagian turbin. Untuk mengetahui pengaruh kerusakan tersebut, dilakukan penelitian. Dari penelitian ini diketahui bahwa hubungan antara efisiensi dan kinerja suatu turbin gas adalah jika performansi naik maka efisiensi akan meningkat. Temperatur masuk turbin dan temperatur keluar turbin akan mempengaruhi kinerja turbin.In Bali, electricity demand is based on PLN data of 446,172 MW. To meet this load requirement PLN Bali relies on four different power plants in Pesanggaran, Gilimanuk, Pemaron, and Pontianak. Most electricity generation in Bali uses Gas Power Plants. In the gas generation of the Bali generation there is damage in the turbine section. To find out the effect of this damage, a study was conducted. From this study it is known that the relationship between efficiency and the performance of a gas turbine is that if the performance rises, efficiency will increase. The turbine intake temperature and turbine exit temperature will affect turbine performance.ANALISA PERFORMA TURBIN GAS TIPE CW251 B11 PADA SYSTEM PEMBANGKITAN LISTRIK TENAGA GAS SEKTOR PEMBANGKITAN BALI
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Kosowski, Krzysztof, and Marian Piwowarski. "Design Analysis of Micro Gas Turbines in Closed Cycles." Energies 13, no. 21 (November 5, 2020): 5790. http://dx.doi.org/10.3390/en13215790.

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The problems faced by designers of micro-turbines are connected with a very small volume flow rate of working media which leads to small blade heights and a high rotor speed. In the case of gas turbines this limitation can be overcome by the application of a closed cycle with very low pressure at the compressor inlet (lower than atmospheric pressure). In this way we may apply a micro gas turbine unit of accepted efficiency to work in a similar range of temperatures and the same pressure ratios, but in the range of smaller pressure values and smaller mass flow rate. Thus, we can obtain a gas turbine of a very small output but of the efficiency typical of gas turbines with a much higher power. In this paper, the results of the thermodynamic calculations of the turbine cycles are discussed and the designed gas turbine flow parts are presented. Suggestions of the design solutions of micro gas turbines for different values of power output are proposed. This new approach to gas turbine arrangement makes it possible to build a gas turbine unit of a very small output and a high efficiency. The calculations of cycle and gas turbine design were performed for different cycle parameters and different working media (air, nitrogen, hydrogen, helium, xenon and carbon dioxide).
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Konishi, Tetsu, Toshishige Ai, Hisato Arimura, and Carlos Koeneke. "A101 DEVELOPMENT OF AIR COOLED COMBUSTOR FOR G SERIES GAS TURBINE(Gas Turbine-1)." Proceedings of the International Conference on Power Engineering (ICOPE) 2009.1 (2009): _1–23_—_1–28_. http://dx.doi.org/10.1299/jsmeicope.2009.1._1-23_.

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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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Dissertations / Theses on the topic "Turbine a gas"

1

Ozmen, Teoman. "Gas Turbine Monitoring System." Master's thesis, METU, 2006. http://etd.lib.metu.edu.tr/upload/12607957/index.pdf.

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In this study, a new gas turbine monitoring system being able to carry out appropriate run process is set up for a gas turbine with 250 kW power rating and its accessories. The system with the mechanical and electrical connections of the required sub-parts is transformed to a kind of the test stand. Performance test result calculation method is described. In addition that, performance evaluation software being able to apply with the completion of the preliminary performance tests is developed for this gas turbine. This system has infrastructure for the gas turbine sub-components performance and aerothermodynamics research. This system is also designed for aviation training facility as a training material for the gas turbine start and run demonstration. This system provides the preliminary gas turbine performance research requirements in the laboratory environment.
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Flesland, Synnøve Mangerud. "Gas Turbine Optimum Operation." Thesis, Norges teknisk-naturvitenskapelige universitet, Institutt for energi- og prosessteknikk, 2010. http://urn.kb.se/resolve?urn=urn:nbn:no:ntnu:diva-12409.

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Many offshore installations are dependent on power generated by gas turbines and a critical issue is that these experience performance deterioration over time. Performance deterioration causes reduced plant efficiency and power output as well as increased environmental emissions. It is therefore of highest importance to detect and control recoverable losses in order to reduce their effect. This thesis project was therefore initiated to evaluate parameters for detecting performance deterioration in addition to document different aspects of gas turbine degradation and performance recovery. Compressor fouling is the largest contributor to performance deterioration. Investigating fouling was therefore the main focus of this study.In the present study the deterioration rates of four different gas turbines were evaluated. When choosing gas turbines it was emphasised to select gas turbines operating under equal conditions but with different washing procedures. In addition to offline washing two of the gas turbines had daily online washing routines and one of the gas turbines run idle wash every 1000 hour between each offline wash. Data was extracted from the monitoring software, TurboWatch, and loaded into Excel files. MATLAB scripts were created to handle the large amount of data and visualize performance trends. Series of two parameters were plotted against each other and the graphs were evaluated.The evaluation showed that an overall trend was that the gas turbine that had been running with online washing continuously over a long period of time had higher performance than the reference engine. For the second gas turbine a daily online washing procedure has recently started. The advantage with the evaluation of this gas turbine was that a good reference engine was available. The two engines were operating under quite similar conditions at the same location in addition to having equal filter systems. Some deterioration trends were possible to detect. For the first period both engines seemed to have quite equal deterioration trends. During the second period no clear trends were seen in corrected CDP and corrected EGT when evaluated for constant GG speed. The compressor efficiency had decreasing trends for both engines during the second period as well, but the compressor efficiency for machine 1 was overall higher during the period with online washing than the previous period. The borescope pictures taken after the first period with online washing showed good visual results. However, it is too premature to make a final decision regarding the exact performance gain of online washing. At the time the study was performed the engine had only been running online washing for one operating interval, and more investigation over longer time is recommended. For the engine running with idle wash it was not possible to conclude on the basis of the collected data. No clear deterioration trends were detected and investigations over longer time and several operating intervals are recommended. It is also important to be aware of the fact that the performance gain of idle wash needs to be much higher than for online washing in order for idle wash to be economically profitable. There are several uncertainties related to performance trends. These include inaccuracy in instrumentation, monitoring software, calibration etc. Due to the fact that all the gas turbines evaluated in this study only have standard instrumentation it caused additional uncertainty in the performance trends. One suggestion for further study is to initiate a test instrumented gas turbine into operation with sensors for measuring inlet pressure depression
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Spencer, Matthew Richard. "Gas turbine lubricant evaluation." Thesis, University of Birmingham, 2014. http://etheses.bham.ac.uk//id/eprint/5423/.

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This thesis is a study of the chemical and physical changes which can occur to gas turbine lubricants as a result of exposure to operational conditions. The continual evolution toward more efficient gas turbines is accompanied by increasing thermal and mechanical loading which the lubricant must be able to withstand. In this thesis two major degradation issues are studied; thermal oxidative degradation and lubricant deposition. In the area of thermal oxidative degradation, efforts are made to better understand the key parameters which determine the lubricant breakdown mechanism. Through control of these parameters and comparison to service derived gas turbine oil samples a new laboratory methodology is proposed for the assessment of lubricant oxidative degradation. The study of lubricant deposition in this thesis is concentrated on the regions of highest risk, the bearing chamber feed (single phase) and vent (two phase) oil pipes. Development of existing laboratory scale deposition simulators was conducted to increase how engine representative the methods are of gas turbine conditions. These simulators were used to evaluate the rate of deposition with a range of lubricants, simulated engine cycles and pipe surfaces.
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Rice, Matthew Jason. "Simulation of Isothermal Combustion in Gas Turbines." Thesis, Virginia Tech, 2004. http://hdl.handle.net/10919/9723.

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Current improvements in gas turbine engine performance have arisen primarily due to increases in turbine inlet temperature and compressor pressure ratios. However, a maximum possible turbine inlet temperature exits in the form of the adiabatic combustion temperature of the fuel. In addition, thermal limits of turbine blade materials also places an upper bound on turbine inlet temperatures. Thus, the current strategy for improving gas turbine efficiency is inherently limited. Introduction of a new gas turbine, based on an alternative work cycle utilizing isothermal combustion (i.e. combustion within the turbine) affords significant opportunities for improving engine output and/or efficiency. However, implementation of such a scheme presents a number of technological challenges such as holding a flame in high-speed flow. The current research is aimed at determining whether such a combustion scheme is feasible using computational methods. The geometry, a simple 2-D cascade utilizes surface injection within the stator or rotor boundary layers (including the rotor pressure side recirculation zone (a natural flame holder). Computational methods utilized both steady and time accurate calculations with transitional flow as well as laminar and turbulent combustion and species transport. It has been determined that burning within a turbine is possible given a variety of injection schemes using "typical" foil geometries under "typical" operating conditions. Specifically, results indicate that combustion is self-igniting and, hence, self-sustaining given the high temperatures and pressures within a high pressure turbine passage. Deterioration of aerodynamic performance is not pronounced regardless of injection scheme. However, increased thermal loading in the form of higher adiabatic surface temperatures or heat transfer is significant given the injection and burning of the fuel within the boundary layer. This increase in thermal loading is, however, minimized when injection takes place in or near a recirculation zone. The effect of injection location on pattern factors indicates that suction side injection minimizes temperature variation downstream of the injection surface (for rotor injection only). In addition, the most uniform temperature profile (in the flow direction) is achieved by injection fuel and combustion nearest to the source of work extraction. Namely, injection at the rotor produces the most "isothermal" temperature distribution. Finally, a pseudo direct simulation of an isothermal machine is conducted by combining simulation data and assumed processes. The results indicate that isothermal combustion results in an increase in turbine specific work and efficiency over the equivalent Brayton cycle.
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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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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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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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Spencer, A. "Gas turbine combustor port flows." Thesis, Loughborough University, 1998. https://dspace.lboro.ac.uk/2134/6883.

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Competitive pressure and stringent emissions legislation have placed an urgent demand on research to improve our understanding of the gas turbine combustor flow field. Flow through the air admission ports of a combustor plays an essential role in determining the internal flow patterns on which many features of combustor performance depend. This thesis explains how a combination of experimental and computational research has helped improve our understanding, and ability to predict, the flow characteristics of jets entering a combustor. The experiments focused on a simplified generic geometry of a combustor port system. Two concentric tubes, with ports introduced into the inner tube's wall, allowed a set of radially impinging jets to be formed within the inner tube. By investigating the flow with LDA instrumentation and flow visualisation methods a quantitative and qualitative picture of the mean and turbulent flow fields has been constructed. Data were collected from the annulus, port and core regions. These data provide suitable validation information for computational models, allow improved understanding of the detailed flow physics and provide the global performance parameters used traditionally by combustor designers. Computational work focused on improving the port representation within CFD models. This work looked at the effect of increasing the grid refinement, and improving the geometrical representation of the port. The desire to model realistic port features led to the development of a stand-alone port modelling module. Comparing calculations of plain-circular ports to those for more realistic chuted port geometry, for example, showed that isothermal modelling methods were able to predict the expected changes to the global parameters measured. Moreover, these effects are seen to have significant consequences on the predicted combustor core flow field.
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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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Pishva, S. M. R. (S Mohammed Reza) Carleton University Dissertation Engineering Mechanical. "Rejuvenation of gas turbine discs." Ottawa, 1988.

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Books on the topic "Turbine a gas"

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Beck, Douglas Stephen. Gas-turbine regenerators. New York: Chapman & Hall, 1996.

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Beck, Douglas Stephen. Gas-turbine regenerators. New York: Chapman & Hall, 1996.

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Beck, Douglas Stephen, and David Gordon Wilson. Gas-Turbine Regenerators. Boston, MA: Springer US, 1996. http://dx.doi.org/10.1007/978-1-4613-1209-3.

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Lieuwen, Tim C., and Vigor Yang, eds. Gas Turbine Emissions. Cambridge: Cambridge University Press, 2013. http://dx.doi.org/10.1017/cbo9781139015462.

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Walsh, Philip P. Gas turbine performance. Oxford: Blackwell Science, 1998.

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Beck, Douglas Stephen. Gas-Turbine Regenerators. Boston, MA: Springer US, 1996.

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Rogers, G. F. C. 1921- and Saravanamuttoo, H. I. H. 1933-, eds. Gas turbine theory. 3rd ed. Harlow: Longman Scientific & Technical, 1987.

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Lefebvre, Arthur Henry. Gas turbine combustion. 2nd ed. Philadelphia: Taylor & Francis, 1999.

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H, Saravanamuttoo H. I., ed. Gas turbine theory. 6th ed. Upper Saddle River, N.J: Pearson Prentice Hall, 2008.

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Walsh, Philip P. Gas turbine performance. Fairfield, NJ: Blackwell Science, 1998.

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Book chapters on the topic "Turbine a gas"

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Beck, Douglas Stephen, and David Gordon Wilson. "Gas-Turbine Cycles." In Gas-Turbine Regenerators, 37–62. Boston, MA: Springer US, 1996. http://dx.doi.org/10.1007/978-1-4613-1209-3_3.

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Beck, Douglas Stephen, and David Gordon Wilson. "Introduction." In Gas-Turbine Regenerators, 1–26. Boston, MA: Springer US, 1996. http://dx.doi.org/10.1007/978-1-4613-1209-3_1.

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Beck, Douglas Stephen, and David Gordon Wilson. "Background." In Gas-Turbine Regenerators, 27–35. Boston, MA: Springer US, 1996. http://dx.doi.org/10.1007/978-1-4613-1209-3_2.

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Beck, Douglas Stephen, and David Gordon Wilson. "Regenerator Designs." In Gas-Turbine Regenerators, 63–78. Boston, MA: Springer US, 1996. http://dx.doi.org/10.1007/978-1-4613-1209-3_4.

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Beck, Douglas Stephen, and David Gordon Wilson. "Design Procedures and Examples." In Gas-Turbine Regenerators, 79–120. Boston, MA: Springer US, 1996. http://dx.doi.org/10.1007/978-1-4613-1209-3_5.

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Beck, Douglas Stephen, and David Gordon Wilson. "Regenerator Performance." In Gas-Turbine Regenerators, 121–233. Boston, MA: Springer US, 1996. http://dx.doi.org/10.1007/978-1-4613-1209-3_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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El Hefni, Baligh, and Daniel Bouskela. "Gas Turbine Modeling." In Modeling and Simulation of Thermal Power Plants with ThermoSysPro, 297–309. Cham: Springer International Publishing, 2019. http://dx.doi.org/10.1007/978-3-030-05105-1_11.

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Gülen, S. Can. "Gas Turbine." In Gas Turbine Combined Cycle Power Plants, 33–74. CRC Press, 2019. http://dx.doi.org/10.1201/9780429244360-4.

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Schnieder, M., and T. Sommer. "Turbines for industrial gas turbine systems." In Modern Gas Turbine Systems, 188–224. Elsevier, 2013. http://dx.doi.org/10.1533/9780857096067.2.188.

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Conference papers on the topic "Turbine a gas"

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Clarke, P. "Gas turbine maintenance." In IEE Colloquium on Development in Mid-Merit Open Cycle Turbine Plants. IEE, 1999. http://dx.doi.org/10.1049/ic:19990662.

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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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Van Leuven, Vern. "Solar Turbines Incorporated “Taurus 60” Gas Turbine Development." In ASME 1994 International Gas Turbine and Aeroengine Congress and Exposition. American Society of Mechanical Engineers, 1994. http://dx.doi.org/10.1115/94-gt-115.

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The Taurus gas turbine was first introduced in 1989 with ratings of 6200 HP for single shaft and 6500 HP for twin shaft configurations. A new design of the single shaft third stage turbine rotor and exhaust diffuser brought its power to 6500 HP in 1991. A program was initiated early in 1992 to identify opportunities to further optimize performance of the Taurus. Thorough investigation of performance sensitivity to thermodynamic cycle parameters has resulted in significant improvement over the original design with no change in firing temperature. Aerodynamic and mechanical design changes were implemented in 1993 which raised Taurus performance to 7000 HP and 32% thermal efficiency. Selection of the final design configuration was the outcome of performance maximization versus cost increase, durability risk and loss of commonality with previous engines. This paper details these changes and the design selection process.
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Niu, Xiying, Feng Lin, Weishun Li, Chen Liang, Shunwang Yu, and Bo Xu. "Gas-Dynamics Design of Reversible Turbine for Marine Gas Turbine Engine." In ASME Turbo Expo 2017: Turbomachinery Technical Conference and Exposition. American Society of Mechanical Engineers, 2017. http://dx.doi.org/10.1115/gt2017-63176.

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Gas turbine engines are widely used as the marine main power system. However, they can’t reverse like diesel engine. If the reversal is realized, other ways must be adopted, for example, controllable pitch propeller (CPP) and reversible gearing. Although CPP has widespread use, the actuator installation inside the hub of the propeller lead to the decrease in efficiency, and it takes one minute to switch “full speed ahead” to “full speed astern”. In addition, some devices need to be added for the reversible gearing, and it takes five minutes to switch from “full speed ahead” “to “full speed astern”. Based on the gas turbine engine itself, a reversible gas turbine engine is proposed, which can rotate positively or reversely. Most important of all, reversible gas turbine engine can realize operating states of “full speed ahead”, “full speed astern“ and “stop propeller”. And, it just takes half of one minute to switch “full speed ahead” to “full speed astern”. Since reversible gas turbine engines have compensating advantages, and especially in recent years computational fluid dynamics (CFD) technology and turbine gas-dynamics design level develop rapidly, reversible gas turbine engines will be a good direction for ship astern. In this paper, the power turbine of a marine gas turbine engine was redesigned by three dimensional shape modification, and the flow field is analyzed using CFD, in order to redesign into a reverse turbine. The last stage vanes and blades of this power turbine were changed to double-layer structure. That is, the outer one is reversible turbine, while the inner is the ahead one. Note that their rotational directions are opposite. In order to realize switching between rotation ahead and rotation astern, switching devices were designed, which locate in the duct between the low pressure turbine and power turbine. Moreover, In order to reduce the blade windage loss caused by the reversible turbine during working ahead, baffle plates were used before and after the reversible rotor blades. This paper mainly studied how to increase the efficiency of the reversible turbine stage, the torque change under different operating conditions, rotational speed and rotational directions, and flow field under typical operating conditions. A perfect profile is expected to provide for reversible power turbine, and it can decrease the blade windage loss, and increase the efficiency of the whole gas turbine engine. Overall, the efficiency of the newly designed reversible turbine is up to 85.7%, and the output power is more than 10 MW, which can meet requirements of no less than 30% power of rated condition. Most importantly, the shaft is not over torque under all ahead and astern conditions. Detailed results about these are presented and discussed in the paper.
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Tsuji, Tadashi. "Performance Analysis On Gas Engine – Gas Turbine Combined Cycle Integrated With Regenerative Gas Turbine." In ASME Turbo Expo 2007: Power for Land, Sea, and Air. ASMEDC, 2007. http://dx.doi.org/10.1115/gt2007-27198.

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The gas engine-gas turbine combined cycle was developed as the ETCS (Engine Turbo Compound System) that has a potential to be a future high performance combined cycle. The reciprocating engine operates with a maximum pressure and temperature in the cylinder, higher than that of the conventional gas turbines. When the gas engine is integrated with a gas turbine instead of a turbocharger, the concept of the ETCS with ERGT (Engine Reheat Gas Turbine) is available. In order to attain a better ETCS performance, a natural gas firing RGT (Regenerative Gas Turbine) was selected as the core gas turbine. For the system integration, the recuperator of RGT was exchanged for a gas engine. Focusing on the effect of engine exhaust temperature, we found that the ETCS cycle with ERGT has the potential to achieve a higher thermal efficiency than that of a re-generative cycle gas turbine with no change of TIT (Turbine Inlet Temperature). The engine exhaust temperature of 900°C increases the system power generation efficiency from 39% of RGT to 45% in ERGT (GT-Gas Engine) and up to 59% in ETCS (GT-Gas Engine-Steam Turbine) (TIT 1200°C).
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MacLeod, J. D., and B. Drbanski. "Turbine Rebuild Effects on Gas Turbine Performance." In ASME 1992 International Gas Turbine and Aeroengine Congress and Exposition. American Society of Mechanical Engineers, 1992. http://dx.doi.org/10.1115/92-gt-023.

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The Engine Laboratory of the National Research Council of Canada (NRCC), with the assistance of Standard Aero Ltd., has established a program for the evaluation of component deterioration on gas turbine engine performance. As part of this project, a study of the effects of turbine rebuild tolerances on overall engine performance was undertaken. This study investigated the range of performance changes that might be expected for simply disassembling and reassembling the turbine module of a gas turbine engine, and how these changes would influence the results of the component fault implantation program. To evaluate the effects of rebuilding the turbine on the performance of a single spool engine, such as Allison T56 turboprop engine, a series of three rebuilds were carried out. This study was performed in a similar way to a previous NRCC study on the effects of compressor rebuilding. While the compressor rebuild study had found performance changes in the order of 1% on various engine parameters, the effects of rebuilding the turbine have proven to be even more significant. Based on the results of the turbine rebuild study, new methods to improve the assurance of the best possible tolerances during the rebuild process are currently being addressed. This paper describes the project objectives, the experimental installation, and the results of the performance evaluations. Discussed are performance variations due to turbine rebuilds on engine performance characteristics. As the performance changes were significant, a rigorous measurement uncertainty analysis is included.
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Millsaps, Knox T., and Bruce Rodman. "Thermodynamic Analysis of “Inter-Turbine” and “Intra-Turbine” Reheat for Marine Gas Turbines." In ASME Turbo Expo 2004: Power for Land, Sea, and Air. ASMEDC, 2004. http://dx.doi.org/10.1115/gt2004-54174.

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This paper presents thermodynamic analyses of two types of reheat combustion cycles in gas turbines and provides an evaluation of their usefulness in marine power and propulsion applications. Specifically, baseline cycles, using components of various technology levels, were compared to cycles with single-stage reheat (inter-turbine reheat), and continuous or constant temperature reheat (intra-turbine reheat). the results of this primary flow path analysis show that reheat can greatly increase the power density, while reducing the total fuel consumption over a standard warship mission profile. These trends are strongest at lower technology levels, but are also present at higher component technology levels.
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Becker, Bernard. "Robust Gas Turbine Design." In ASME Turbo Expo 2002: Power for Land, Sea, and Air. ASMEDC, 2002. http://dx.doi.org/10.1115/gt2002-30159.

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Industrial gas turbines utilize numerous design features that cannot be implemented in jet aircraft turbines for weight reasons, but because of their straight-forward and robust nature trim costs and reduce both maintenance effort and operating risks. Regardless of manufacturer, the following design features, for example, have become the established industry standard: • single-shaft rotor; • 2 bearings at atmospheric pressure; • Journal bearing instead of ball bearings; • steel blading in the compressor. For the key components compressor, turbine, rotor, and combustion chamber of its 3A family (Fig. 1), Siemens has developed and tested additional features that reduce wear further and improve operational reliability. Operating experience gathered to date has shown that these features enable achievements of very high reliability and availability. Some of the measures described also contribute to enhanced output and efficiency.
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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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Harmeyer, Jerome E. "ICR Gas Turbine Update." 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-429.

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The Intercooled, Recuperated (ICR) marine gas turbine development program is a U.S. Navy program to design, develop, and qualify an engine for propulsion of future surface ships. This paper provides a brief description of the program objectives, technical requirements, design overview, and status of development program and the test program currently underway. The engine system being developed is designated the WR-21 and is being designed in accordance with a detailed technical specification issued by the U.S. Navy.
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Reports on the topic "Turbine a gas"

1

Epstein, A. H., K. S. Breuer, J. H. Lang, M. A. Schmidt, and S. D. Senturia. Micro Gas Turbine Generators. Fort Belvoir, VA: Defense Technical Information Center, December 2000. http://dx.doi.org/10.21236/ada391343.

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Pint, Bruce A., Michael M. Kirka, Gary S. Marlow, Charles S. Hawkins, Jim Kesseli, and Jim Nash. Internally Cooled Turbine Rotor for Small Gas Turbine. Office of Scientific and Technical Information (OSTI), November 2017. http://dx.doi.org/10.2172/1427664.

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

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

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Metz, Stephen D., and David L. Smith. Survey of Gas Turbine Control for Application to Marine Gas Turbine Propulsion System Control. Fort Belvoir, VA: Defense Technical Information Center, January 1989. http://dx.doi.org/10.21236/ada204713.

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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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