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1
Tafti, Danesh K., Long He, and K. Nagendra. "Large eddy simulation for predicting turbulent heat transfer in gas turbines." Philosophical Transactions of the Royal Society A: Mathematical, Physical and Engineering Sciences 372, no. 2022 (August 13, 2014): 20130322. http://dx.doi.org/10.1098/rsta.2013.0322.
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Blade cooling technology will play a critical role in the next generation of propulsion and power generation gas turbines. Accurate prediction of blade metal temperature can avoid the use of excessive compressed bypass air and allow higher turbine inlet temperature, increasing fuel efficiency and decreasing emissions. Large eddy simulation (LES) has been established to predict heat transfer coefficients with good accuracy under various non-canonical flows, but is still limited to relatively simple geometries and low Reynolds numbers. It is envisioned that the projected increase in computational power combined with a drop in price-to-performance ratio will make system-level simulations using LES in complex blade geometries at engine conditions accessible to the design process in the coming one to two decades. In making this possible, two key challenges are addressed in this paper: working with complex intricate blade geometries and simulating high-Reynolds-number ( Re ) flows. It is proposed to use the immersed boundary method (IBM) combined with LES wall functions. A ribbed duct at Re =20 000 is simulated using the IBM, and a two-pass ribbed duct is simulated at Re =100 000 with and without rotation (rotation number Ro =0.2) using LES with wall functions. The results validate that the IBM is a viable alternative to body-conforming grids and that LES with wall functions reproduces experimental results at a much lower computational cost.
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Jain, Nishan, Luis Bravo, Dokyun Kim, Muthuvel Murugan, Anindya Ghoshal, Frank Ham, and Alison Flatau. "Massively Parallel Large Eddy Simulation of Rotating Turbomachinery for Variable Speed Gas Turbine Engine Operation." Energies 13, no. 3 (February 6, 2020): 703. http://dx.doi.org/10.3390/en13030703.
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Gas turbine engines are required to operate at both design and off-design conditions that can lead to strongly unsteady flow-fields and aerodynamic losses severely impacting performance. Addressing this problem requires effective use of computational fluid dynamics tools and emerging models that resolve the large scale fields in detail while accurately modeling the under-resolved scale dynamics. The objective of the current study is to conduct massively parallel large eddy simulations (LES) of rotating turbomachinery that handle the near-wall dynamics using accurate wall models at relevant operating conditions. The finite volume compressible CharLES solver was employed to conduct the simulations over moving grids generated through Voronoi-based unstructured cells. A grid sensitivity analysis was carried out first to establish reliable parameters and assess the quality of the results. LES simulations were then conducted to understand the impact of blade tip clearance and operating conditions on the stage performance. Variations in tip clearance of 3% and 16% chord were considered in the analysis. Other design points included operation at 100% rotor speed and off-design conditions at 75% and 50% of the rotor speed. The simulation results showed that the adiabatic efficiency improves dramatically with reduction in tip gap due to the decrease in tip leakage flow and the resulting flow structures. The analysis also showed that the internal flow becomes highly unsteady, undergoing massive separation, as the rotor speed deviates from the design point. This study demonstrates the capability of the framework to simulate highly turbulent unsteady flows in a rotating turbomachinery environment. The results provide much needed insight and massive data to investigate novel design concepts for the US Army Future Vertical Lift program.
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Yanin, V. "The contribution of designer L.S. Lebedyanskyi to the development of the gas turbine locomotives." History of science and technology 7, no. 10 (March 30, 2017): 103–8. http://dx.doi.org/10.32703/2415-7422-2017-7-10-103-108.
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Nakazawa, N., H. Ogita, M. Takahashi, T. Yoshizawa, and Y. Mori. "Radial Turbine Development for the 100 kW Automotive Ceramic Gas Turbine." Journal of Engineering for Gas Turbines and Power 120, no. 1 (January 1, 1998): 172–78. http://dx.doi.org/10.1115/1.2818071.
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The development of turbine components for the automotive 100 kW ceramic gas turbine has entered the final stage of the seven-year project and is making satisfactory progress toward the goals. We have attained the interim targets of the aerodynamic performances and have been carrying out tests to further improve efficiency. As for ceramic parts, we have changed the material of the turbine rotor to a new one that is excellent in long-sustained and high-temperature strength properties, and have confirmed substantial strength at high temperature through hot-spin tests. After evaluating blade-vibration stress through analyses and experiments, we completed an endurance evaluation at 1200°C (1473 K) TIT (Turbine Inlet Gas Temperature) and a rated speed of 100,000 rpm. We are now carrying out endurance tests at 1350°C (1623 K) TIT. For ceramic stationary parts, we already finished the evaluations at 1200°C TIT and are also conducting an endurance test at 1350°C TIT. Using these parts in a full-assembly test, together with other elements, we confirmed that they cause no functional problem in tests performed at 1200°C TIT level up to the rated speed (100,000 rpm), and are evaluating their performances.
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Gašparovič, Dominik, Marián Výžinkár, Jozef Žarnovský, and Jan Blata. "Turbine Modification of Nuovo Pignone Gas Turbine." Acta Technologica Agriculturae 20, no. 3 (September 1, 2017): 74–77. http://dx.doi.org/10.1515/ata-2017-0015.
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Abstract This paper deals with the environmental aspects of combustor modification on Nuovo Pignone gas turbines. The mentioned company is engaged in the transport of natural gas to the Slovak Republic and further to other European markets. Legislation considering emissions is getting stricter every year. Original Nuovo Pignone gas turbines would not be able to meet the required emission limits for NOx and COr determined by legislation. Therefore, the company decided to modify seven gas turbines. Due to this reason, the combustion sections had to be replaced with a dry low emission system. These modifications were aimed at improvement of impacts of temperature on the emissions of NOx, since the NOx emissions are defined as thermal (there is an increase in emissions with the increase in temperature). Emissions were monitored continuously by an emission monitoring system (these data are continuously sent to the Office of Environment) and manually by a HORIBA PG-250 analyser. Gas delivery point is located in the flue pipeline, and data was processed by means of PC after reaching this point. The results lead us to conclusion that modification was an efficient and good solution in terms of economy, because this solution reduced emissions (from 300 mg·m−3 to 50 mg·m−3) and contributed to meeting of the stricter emission limits (from 370 mg·m−3 to 100 mg·m−3). Monitoring of the impacts of growing performance of equipment on emissions represents a possibility for further development of science in this field.
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Basha, Mehaboob, S. M. Shaahid, and Luai Al-Hadhrami. "Impact of Gas Turbine Frame Size on Efficiency of Gas Turbine Power Plants." Applied Mechanics and Materials 492 (January 2014): 447–52. http://dx.doi.org/10.4028/www.scientific.net/amm.492.447.
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A computational study to assess the effect of gas turbine (GT) frame size on efficiency of gas turbine power plant configurations is presented in this paper. The work includes the effect of relative humidity (RH), ambient inlet air temperature and frame size on gas turbine plant configurations with and without fogger unit. Investigation also covers economic analysis. 20 MWe GE 5271RA, 40 MWe GE-6561B and 70 MWe GE-6101FA frames are selected for the present study. GT PRO software has been used for carrying out the analysis including; net plant output and net efficiency, break even electricity price (BEEP) and break even fuel LHV price (BEFP), etc. The relative humidity and temperature have been varied from 30 to 45 % and from 80 to 100° F, respectively. Fuels considered in the study are natural gas, diesel and crude oil. Results show that variation of humidity does not affect the gas turbine performance appreciably for all GT frame size regardless of type of fuel. For a decrease of inlet air temperature by 10 °F, net plant output and efficiency have been found to increase by 4 and 1.7 %, 4.2 and 1.3 %, 4.7 and 1.8 %, respectively for 20 MW,40MW and 70MW for crude oil and for GT only situation. However, for GT with Fogger scenario, for a decrease of inlet air temperature by 10 °F, net plant output and efficiency have been found to further increase by 3.1 and 1.3 %, 3 and 0.9 %, 3.2 and 1.1 %, respectively for 20 MW,40MW and 70MW. For situations with and without fogger for crude oil, BEFP have been found to vary from 1.3968 to 1.3916, 2.13 to 2.0948, 2.387 to 2.4642 USD/MMBTU respectively for 20 MW, 40MW and 70MW and BEEP have been found to vary from 0.03142 to 0.0313, 0.02488 to 0.02504, 0.0229 to 0.0233 USD/kWh respectively for 20 MW, 40MW and 70MW.
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Lim, Hyung-Soo, Je-Sung Bang, Bum-Seog Choi, Moo-Ryong Park, Jun-Young Park, Jeongmin Seo, Soon-Chan Hwang, Jeong Lak Sohn, and Byung Ok Kim. "Secondary flow stabilization of 100 kW-class micro gas turbine." Journal of Mechanical Science and Technology 31, no. 4 (April 2017): 1753–61. http://dx.doi.org/10.1007/s12206-017-0323-x.
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Ahmad Zahidin, A. A., A. M. I. Mamat, and A. Romagnoli. "Computational performance of a-100 kW low pressure turbine to recover gas turbine exhaust energy." Journal of Mechanical Engineering and Sciences 13, no. 2 (June 28, 2019): 4777–93. http://dx.doi.org/10.15282/jmes.13.2.2019.02.0399.
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Low Pressure Turbine (LPT) was designed to recover exhaust energy from Internal Combustion (IC) engine. The LPT is located downstream retrieved exhaust heat energy from combustion after flowing through the high pressure turbine (HPT). The work output obtained from the exhaust energy is used to drive an electric generator with power output of 1.0kW. These was not done by commercial turbine as the low efficiency resulted when operated. The main purpose of this project is to develop a scaling model for LPT with power output up to 100kW. An existing LPT that was designed with output of 1.0 kW used as guideline to upscale the turbine. Scaling factor was obtained by comparing the baseline with power output. The turbine performance was analysed by using a commercial Computational Fluid Dynamic (CFD) ANSYS CFX. The study found that the scaling factor f, of 10 can be used to produce a 100kW at passage. Thus, the geometrical parameter will be scaled accordingly. The rotational speed is reduced from 50,000 rpm to 5,000 rpm. The CFD analysis found that 81% of total-static efficiency, ht-s at velocity ratio VR, of 0.68 and the Pressure Ratio PR, of 1.12 producing power of 119.88 kW which nearest with the design point which is at 100 kW. Despite the LPT swallowing capacity is increased by 50 times, the LPT is still limited by the operational choking Pressure Ratio, PR limitation which is 1.4.
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Eidensten, L., J. Yan, and G. Svedberg. "Biomass Externally Fired Gas Turbine Cogeneration." Journal of Engineering for Gas Turbines and Power 118, no. 3 (July 1, 1996): 604–9. http://dx.doi.org/10.1115/1.2816691.
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This paper is a presentation of a systematic study on externally fired gas turbine cogeneration fueled by biomass. The gas turbine is coupled in series with a biomass combustion furnace in which the gas turbine exhaust is used to support combustion. Three cogeneration systems have been simulated. They are systems without a gas turbine, with a non-top-fired gas turbine, and a top-fired gas turbine. For all systems, three types of combustion equipment have been selected: circulating fluidized bed (CFB) boiler, grate fired steam boiler, and grate fired hot water boiler. The sizes of biomass furnaces have been chosen as 20 MW and 100 MW fuel inputs. The total efficiencies based on electricity plus process heat, electrical efficiencies, and the power-to-heat ratios for various alternatives have been calculated. For each of the cogeneration systems, part-load performance with varying biomass fuel input is presented. Systems with CFB boilers have a higher total efficiency and electrical efficiency than other systems when a top-fired gas turbine is added. However, the systems with grate fired steam boilers allow higher combustion temperature in the furnace than CFB boilers do. Therefore, a top combustor may not be needed when high temperature is already available. Only one low-grade fuel system is then needed and the gas turbine can operate with a very clean working medium.
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Taylor, R. P. "Surface Roughness Measurements on Gas Turbine Blades." Journal of Turbomachinery 112, no. 2 (April 1, 1990): 175–80. http://dx.doi.org/10.1115/1.2927630.
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Results are presented from profilometer measurements of the surface roughness on in-service turbine engine blades from F-100 and TF-39 aeroengines. On each blade, one roughness profile is taken in the region of the leading edge, the midchord and the trailing edge on both the pressure and suction sides for a total of six profiles. Thirty first-stage turbine blades are measured from each engine. Statistical computations are performed on these profiles and the root mean square height, skewness and kurtosis of the roughness height distribution are presented along with the correlation length of the autocorrelation function. The purpose of this work is to provide insight into the nature of surface roughness characteristics of in-service turbine blades which can be used in the development of scaled laboratory experiments of boundary layer flow and heat transfer on turbine engine blades.
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Bhargava, R., M. Bianchi, G. Negri di Montenegro, and A. Peretto. "Thermo-Economic Analysis of an Intercooled, Reheat and Recuperated Gas Turbine for Cogeneration Applications–Part I: Base Load Operation." Journal of Engineering for Gas Turbines and Power 124, no. 1 (February 1, 2000): 147–54. http://dx.doi.org/10.1115/1.1413463.
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This paper presents a thermo-economic analysis of an intercooled, reheat (ICRH) gas turbine, with and without recuperation, for cogeneration applications. The optimization analyses of thermodynamic parameters have permitted to calculate variables, such as low-pressure compressor pressure ratio, high-pressure turbine pressure ratio and gas temperature at the waste heat recovery unit inlet while maximizing electric efficiency and “Energy Saving Index.” Subsequently, the economic analyses have allowed to evaluate return on the investment, and the minimum value of gross payout period, for the cycle configurations of highest thermodynamic performance. In the present study three sizes (100 MW, 20 MW, and 5 MW) of gas turbines have been examined. The performed investigation reveals that the maximum value of electric efficiency and “Energy Saving Index” is achieved for a large size (100 MW) recuperated ICRH gas turbine based cogeneration system. However, a nonrecuperated ICRH gas turbine (of 100 MW) based cogeneration system provides maximum value of return on the investment and the minimum value of gross payout period compared to the other gas turbine cycles, of the same size and with same power to heat ratio, investigated in the present study. A comprehensive thermo-economic analysis methodology, presented in this paper, should provide useful guidelines for preliminary sizing and selection of gas turbine cycle for cogeneration applications.
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Deng, Chao, Ahmed N. Abdalla, Thamir K. Ibrahim, MingXin Jiang, Ahmed T. Al-Sammarraie, and Jun Wu. "Implementation of Adaptive Neuro-fuzzy Model to Optimize Operational Process of Multiconfiguration Gas-Turbines." Advances in High Energy Physics 2020 (July 3, 2020): 1–17. http://dx.doi.org/10.1155/2020/6590138.
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In this article, the adaptive neuro-fuzzy inference system (ANFIS) and multiconfiguration gas-turbines are used to predict the optimal gas-turbine operating parameters. The principle formulations of gas-turbine configurations with various operating conditions are introduced in detail. The effects of different parameters have been analyzed to select the optimum gas-turbine configuration. The adopted ANFIS model has five inputs, namely, isentropic turbine efficiency (Teff), isentropic compressor efficiency (Ceff), ambient temperature (T1), pressure ratio (rp), and turbine inlet temperature (TIT), as well as three outputs, fuel consumption, power output, and thermal efficiency. Both actual reported information, from Baiji Gas-Turbines of Iraq, and simulated data were utilized with the ANFIS model. The results show that, at an isentropic compressor efficiency of 100% and turbine inlet temperature of 1900 K, the peak thermal efficiency amounts to 63% and 375 MW of power resulted, which was the peak value of the power output. Furthermore, at an isentropic compressor efficiency of 100% and a pressure ratio of 30, a peak specific fuel consumption amount of 0.033 kg/kWh was obtained. The predicted results reveal that the proposed model determines the operating conditions that strongly influence the performance of the gas-turbine. In addition, the predicted results of the simulated regenerative gas-turbine (RGT) and ANFIS model were satisfactory compared to that of the foregoing Baiji Gas-Turbines.
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Nosov, N. V., A. D. Abramov, and S. I. Kosulin. "Assessment of gas turbine engine airfoil surface microstructure." VESTNIK of Samara University. Aerospace and Mechanical Engineering 16, no. 2 (July 20, 2017): 90. http://dx.doi.org/10.18287/2541-7533-2017-16-2-90-100.
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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 (June 19, 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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Epstein, Alan H. "Millimeter-Scale, Micro-Electro-Mechanical Systems Gas Turbine Engines." Journal of Engineering for Gas Turbines and Power 126, no. 2 (April 1, 2004): 205–26. http://dx.doi.org/10.1115/1.1739245.
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The confluence of market demand for greatly improved compact power sources for portable electronics with the rapidly expanding capability of micromachining technology has made feasible the development of gas turbines in the millimeter-size range. With airfoil spans measured in 100’s of microns rather than meters, these “microengines” have about 1 millionth the air flow of large gas turbines and thus should produce about one millionth the power, 10–100 W. Based on semiconductor industry-derived processing of materials such as silicon and silicon carbide to submicron accuracy, such devices are known as micro-electro-mechanical systems (MEMS). Current millimeter-scale designs use centrifugal turbomachinery with pressure ratios in the range of 2:1 to 4:1 and turbine inlet temperatures of 1200–1600 K. The projected performance of these engines are on a par with gas turbines of the 1940s. The thermodynamics of MEMS gas turbines are the same as those for large engines but the mechanics differ due to scaling considerations and manufacturing constraints. The principal challenge is to arrive at a design which meets the thermodynamic and component functional requirements while staying within the realm of realizable micromachining technology. This paper reviews the state of the art of millimeter-size gas turbine engines, including system design and integration, manufacturing, materials, component design, accessories, applications, and economics. It discusses the underlying technical issues, reviews current design approaches, and discusses future development and applications.
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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 (April 1, 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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Itoh, T., and H. Kimura. "Status of the Automotive Ceramic Gas Turbine Development Program." Journal of Engineering for Gas Turbines and Power 115, no. 1 (January 1, 1993): 42–50. http://dx.doi.org/10.1115/1.2906684.
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A seven-year program, designated “Research and Development of Automotive CGT,” commenced in June 1990 with the object of demonstrating the potential advantages of ceramic gas turbine engines for automotive use. This program has been conducted by the Petroleum Energy Center (PEC) with the support of the Ministry of International Trade and Industry. The engine demonstration project in this program is being handled by a team from Japan Automobile Research Institute, Inc. (JARI). This paper describes the activities of the first year of the seven-year program, and includes the project goals and objectives, the program schedule, and the first-stage design of an experimental automotive ceramic gas turbine (CGT) engine and its components. The basic engine is a 100 kW, single-shaft gas turbine engine having a turbine inlet temperature of 1350°C and a rotor speed of 110,000 rpm. The primary engine components including the turbine hot flow path components have been designed using monolithic ceramics and are scheduled to be produced during the second year of the program.
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Griffin, Timothy, Sven Gunnar Sundkvist, Knut A˚sen, and Tor Bruun. "Advanced Zero Emissions Gas Turbine Power Plant." Journal of Engineering for Gas Turbines and Power 127, no. 1 (January 1, 2005): 81–85. http://dx.doi.org/10.1115/1.1806837.
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The AZEP “advanced zero emissions power plant” project addresses the development of a novel “zero emissions,” gas turbine-based, power generation process to reduce local and global CO2 emissions in the most cost-effective way. Process calculations indicate that the AZEP concept will result only in a loss of about 4% points in efficiency including the pressurization of CO2 to 100 bar, as compared to approximately 10% loss using conventional tail-end CO2 capture methods. Additionally, the concept allows the use of air-based gas turbine equipment and, thus, eliminates the need for expensive development of new turbomachinery. The key to achieving these targets is the development of an integrated MCM-reactor in which (a) O2 is separated from air by use of a mixed-conductive membrane (MCM), (b) combustion of natural gas occurs in an N2-free environment, and (c) the heat of combustion is transferred to the oxygen-depleted air by a high temperature heat exchanger. This MCM-reactor replaces the combustion chamber in a standard gas turbine power plant. The cost of removing CO2 from the combustion exhaust gas is significantly reduced, since this contains only CO2 and water vapor. The initial project phase is focused on the research and development of the major components of the MCM-reactor (air separation membrane, combustor, and high temperature heat exchanger), the combination of these components into an integrated reactor, and subsequent scale-up for future integration in a gas turbine. Within the AZEP process combustion is carried out in a nearly stoichiometric natural gas/O2 mixture heavily diluted in CO2 and water vapor. The influence of this high exhaust gas dilution on the stability of natural gas combustion has been investigated, using lean-premix combustion technologies. Experiments have been performed both at atmospheric and high pressures (up to 15 bar), simulating the conditions found in the AZEP process. Preliminary tests have been performed on MCM modules under simulated gas turbine conditions. Additionally, preliminary reactor designs, incorporating MCM, heat exchanger, and combustor, have been made, based on the results of initial component testing. Techno-economic process calculations have been performed indicating the advantages of the AZEP process as compared to other proposed CO2-free gas turbine processes.
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Hariyanto, Beny, and Romy Romy. "Maintenance Schedule Optimization for Turnaround Hot Gas Path Inspection of Gas Turbine in North Duri Cogeneration Plant Using Impact Method." Journal of Ocean, Mechanical and Aerospace -science and engineering- (JOMAse) 64, no. 1 (March 30, 2020): 25–32. http://dx.doi.org/10.36842/jomase.v64i1.159.
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North Duri Cogeneration Plant (NDC) is once of Chevron asset in IndoAsia Business Unit. The NDC location is in Duri, Province of Riau, Indonesia. The NDC has 3 units gas turbine and each unit has been combined with Heat Recovery Steam Generator (HRSG). An unit gas turbine NDC is produce electricity of 100 MW, and 1 unit of HRSG NDC that is produce steam of 360,000 BCWEPD (Barrel Cool Water Equivalent per Day). Hot gas path inspection (HGPI) is maintenance activities gas turbine, which routine scheduled in NDC every 3 years per unit. Maintenance schedule for turnaround HGPI gas turbine at NDC should be optimizing. By optimized of HGPI maintenance schedule can be maximized work plan, which is comply of 4 Key Performance Indicators there are Safety, Quality, Schedule and Cost through Initiative for Managing PA Cesetter Turnarounds (IMPACT). The result of optimal electricity production was increased by 13,174 MWh and the steam generated from units in NDC of mass total steam of 126,661 Mlbm and 371,827 BSPD.
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Youn, Hee-Chul, and Chang-Ki Woo. "Cause of Fatigue Failure of the First Blade of 100-MW Gas Turbine." Journal of the Korean Society of Manufacturing Technology Engineers 24, no. 6 (December 15, 2015): 632–38. http://dx.doi.org/10.7735/ksmte.2015.24.6.632.
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Zhang, Xiaotao, Xiang Liu, Haoliang Mu, Wenxian Zhang, and Aijun Wang. "Research on Modeling and Control of a 100 kW Micro Bio-Gas Turbine." Journal of Power and Energy Engineering 09, no. 02 (2021): 1–6. http://dx.doi.org/10.4236/jpee.2021.92001.
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Joo, S., S. Kwak, S. Kim, J. Lee, and Y. Yoon. "High-frequency transition characteristics of synthetic natural gas combustion in gas turbine." Aeronautical Journal 123, no. 1259 (January 2019): 138–56. http://dx.doi.org/10.1017/aer.2018.150.
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AbstractIn this study, the combustion instability and emission characteristics of flames of different H2/CH4 compositions were investigated in a partially premixed model gas turbine combustor. A mode shift in the frequency of instability occurred under varying experimental conditions from the first to the seventh mode of longitudinal frequency in the combustor, and a parametric study was conducted to determine the reasons for this shift by using the length of the combustor, a factor that determines the mode frequency of longitudinal instability, as the main parameter. Furthermore, heat load and fuel composition (H2 ratio) were considered as parameters to compare the phenomenon under different conditions. The GRI-3.0 CANTERA code, OH chemiluminescence and the Abel inversion process were applied to analyse the frequency mode shift. NOx emissions, which occurred through the thermal NOx mechanism, increased with increasing heat load and H2 ratio. The instability frequency shifted from the first to the seventh mode as the H2 ratio increased in the H2/CH4 mixture. However, 100% H2 as fuel did not cause combustion instability because it has a higher burning velocity and extinction stretch rate than CH4. Furthermore, the laminar flame speed influenced the frequency mode shift. These phenomena were confirmed by the flame shapes. The Abel inversion process was applied to obtain the cross section of the flames from averaged OH chemiluminescence images. Stable and unstable flames were identified from the radial profile of OH concentration. The combustor length was found to not influence frequency mode shift, whereas the H2 ratio significantly influenced it as well as the flame shape. The results of this experimental study can help in the reliable operation of gas turbine systems in SNG plants.
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Perevoschikov, S. I. "CALCULATION OF EFFECTIVE COMBUSTION PRODUCTS TEMPERATURE BEFORE THE GAS-TURBINE ENGINES POWER TURBINES." Oil and Gas Studies, no. 1 (February 28, 2016): 100–106. http://dx.doi.org/10.31660/0445-0108-2016-1-100-106.
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The article describes derivation of relationships permitting to calculate the temperature of combustion products before the power turbines of gas-turbine engines taking into account a partial return of the lost earlier power of the combustion products in the previous turbines. Using these relationships data significantly improves determination of the gas-turbine engines effective output by their operation data.
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Reale, Fabrizio, Raffaela Calabria, Fabio Chiariello, Rocco Pagliara, and Patrizio Massoli. "A Micro Gas Turbine Fuelled by Methane-Hydrogen Blends." Applied Mechanics and Materials 232 (November 2012): 792–96. http://dx.doi.org/10.4028/www.scientific.net/amm.232.792.
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The combustion efficiency and the gaseous emission of a 100 kWe MGT, designed for working with natural gas but fuelled with blends containing up to 10% of hydrogen is investigated. A critical comparison between experimental data and results of the CFD analysis of the combustor is discussed. The k-epsilon RANS turbulence model and the Finite Rate – Eddy Dissipation combustion model were used in the numerical computations. The chemical kinetic mechanisms embedded were the 2-step Westbrook and Dryer for methane oxidation, 1-step Westbrook and Dryer for hydrogen oxidation and the Zeldovich mechanism for NO formation. The experimental data and numerical computations are in agreement within the experimental accuracy for NO emissions. Regarding CO, there is a significant deviation between experimental and computational data due to the scarce predictive capability of the simple two steps kinetic mechanism was adopted. From a practical point of view, the possibility of using fuels with a similar Wobbe index was confirmed. In particular the addiction of 10 % of hydrogen to pure methane doesn’t affect the behavior of the micro gas turbine either in terms of NO or CO emissions.
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Adib, Muhammad. "Analysis of Ambient Temperature Effect on Gas Turbine Centaur 40 at Sepinggan Production Field, Chevron Indonesia Company." Jurnal Teknik Mesin ITI 3, no. 2 (October 29, 2019): 29. http://dx.doi.org/10.31543/jtm.v3i2.262.
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Gas turbine Centaur 40 drive gas compressor operates 24 hours a day and continuously with monitored output parameters, namely pressure and the gas flow capacity In its operation, it is often found that the optimal output parameters are generated during low ambient temperatures, for example in the night, cloudy and rainy. This study is aimed to determine the effect of changes in ambient temperature on the gas turbine power. During operation and research was done, the independent variable used is ambient temperature at 24 – 33 0C at constant 100% rotation of the turbine shaft. The decrease in gas turbine performance is seen from the increase in Specific Fuel Consumption (SFC), a decrease in the power produced and thermal efficiency. Specific fuel consumption value from the calculation results is 0.06072 kg/kW.h at 24 0C ambient temperature and 0.06565 kg/kW.h at 33 0C ambient temperature. Power produced by the power turbine is 3532,657 HP at 24 0C ambient temperature and 3046,557 HP at 33 0C ambient temperature, while the thermal efficiency cycle is 54,159% at 24 0C ambient temperature and 49,727% at 33 0C ambient temperature. Keywords: gas turbine, ambient temperature, specific fuel consumption, thermal efficiency.
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Pattanayak, Lalatendu. "Thermodynamic modeling and Exergy Analysis of Gas Turbine Cycle for Different Boundary conditions." International Journal of Power Electronics and Drive Systems (IJPEDS) 6, no. 2 (June 1, 2015): 205. http://dx.doi.org/10.11591/ijpeds.v6.i2.pp205-215.
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In this study an exergy analysis of 88.71 MW 13D2 gas turbine (GT) topping cycle is carried out. Exergy analysis based on second law was applied to the gas cycle and individual components through a modeling approach. The analysis shows that the highest exergy destruction occurs in the combustion chamber (CC). In addition, the effects of the gas turbine load and performance variations with ambient temperature, compression ratio and turbine inlet temperature (TIT) are investigated to analyse the change in system behavior. The analysis shows that the gas turbine is significantly affected by the ambient temperature which leads to a decrease in power output. The results of the load variation of the gas turbine show that a reduction in gas turbine load results in a decrease in the exergy efficiency of the cycle as well as all the components. The compressor has the largest exergy efficiency of 92.84% compared to the other component of the GT and combustion chamber is the highest source of exergy destruction of 109.89 MW at 100 % load condition. With increase in ambient temperature both exergy destruction rate and exergy efficiency decreases.
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Lubbock, RJ, and MLG Oldfield. "Turbulent velocity and pressure fluctuations in gas turbine combustor exit flows." Proceedings of the Institution of Mechanical Engineers, Part A: Journal of Power and Energy 232, no. 4 (September 26, 2017): 337–49. http://dx.doi.org/10.1177/0957650917732885.
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This paper presents the results of two test programmes using novel instrumentation to characterise the pressure and turbulent velocity fields in gas-turbine combustor exit flows. The probes are uncooled, therefore a fast-insertion traverse system is employed to prevent thermal degradation of the instrumentation in these severely hostile high-temperature environments. High-bandwidth ultra-miniature pressure transducers are used to measure unsteady total pressure, whilst a Pitot tube is employed to measure time-averaged total pressure. The probes are 4 mm in diameter with a measurement bandwidth of the order of 100 kHz. In the first test programme, the probes are used to characterise the streamwise turbulent velocity field approximately two axial chords downstream of an uncooled single-stage turbine in a turbojet engine. Established data reduction methods and calibration against a hot-wire are used to obtain turbulent velocity fluctuations from unsteady total pressure measurements. Comprehensive turbulence results are presented including time-histories, power spectra, intensities, and lengthscales obtained at four-engine conditions and at two radial and two circumferential measurement locations. In the second test programme the probes are demonstrated in an industrial combustor rig, featuring a can combustor with swirler nozzle and no dilution holes, at temperatures up to 1500 K. Static pressure fluctuations are obtained up to 100 kHz, and some typical combustor spectral features are identified.
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Kim, J., M. G. Dunn, A. J. Baran, D. P. Wade, and E. L. Tremba. "Deposition of Volcanic Materials in the Hot Sections of Two Gas Turbine Engines." Journal of Engineering for Gas Turbines and Power 115, no. 3 (July 1, 1993): 641–51. http://dx.doi.org/10.1115/1.2906754.
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This paper reports the results of a series of tests designed to determine the melting and subsequent deposition behavior of volcanic ash cloud materials in modern gas turbine engine combustors and high-pressure turbine vanes. The specific materials tested were Mt. St. Helens ash and a soil blend containing volcanic ash (black scoria) from Twin Mountain, NM. Hot section test systems were built using actual engine combustors, fuel nozzles, ignitors, and high-pressure turbine vanes from an Allison T56 engine can-type combustor and a more modern Pratt and Whitney F-100 engine annular-type combustor. A rather large turbine inlet temperature range can be achieved using these two combustors. The deposition behavior of volcanic materials as well as some of the parameters that govern whether or not these volcanic ash materials melt and are subsequently deposited are discussed.
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Feitelberg, A. S., and M. A. Lacey. "The GE Rich-Quench-Lean Gas Turbine Combustor." Journal of Engineering for Gas Turbines and Power 120, no. 3 (July 1, 1998): 502–8. http://dx.doi.org/10.1115/1.2818173.
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The General Electric Company has developed and successfully tested a full-scale, F-class (2550°F combustor exit temperature), rich-quench-lean (RQL) gas turbine combustor, designated RQL2, for low heating value (LHV) fuel and integrated gasification combined cycle applications. Although the primary objective of this effort was to develop an RQL combustor with lower conversion of fuel bound nitrogen to NOx than a conventional gas turbine combustor, the RQL2 design can be readily adapted to natural gas and liquid fuel combustion. RQL2 is the culmination of a 5 year research and development effort that began with natural gas tests of a 2” diameter perforated plate combustor and included LHV fuel tests of RQL1, a reduced scale (6” diameter) gas turbine combustor. The RQL2 combustor includes a 14” diameter converging rich stage liner, an impingement cooled 7” diameter radially-stratified-quench stage, and a backward facing step at the entrance to a 10” diameter film cooled lean stage. The rich stage combustor liner has a novel double-walled structure with narrow circumferential cooling channels to maintain metal wall temperatures within design limits. Provisions were made to allow independent control of the air supplied to the rich and quench/lean stages. RQL2 has been fired for almost 100 hours with LHV fuel supplied by a pilot scale coal gasification and high temperature desulfurization system. At the optimum rich stage equivalence ration NOx emissions were about 50 ppmv (on a dry, 15 percent O2 basis), more than a factor of 3 lower than expected from a conventional diffusion flame combustor burning the same fuel. With 4600 ppmv NH3 in the LHV fuel, this corresponds to a conversion of NH3 to NOx of about 5 percent. As conditions were shifted away from the optimum, RQL2 NOx emissions gradually increased until they were comparable to a standard combustor. A chemical kinetic model of RQL2, constructed from a series of ideal chemical reactors, matched the measured NOx emissions fairly well. The CO emissions were between 5 and 30 ppmv (on a dry, 15 percent O2 basis) under all conditions.
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Fadhil, Siti Sarah Ain, Hasril Hasini, Mohd Nasharuddin Mohd Jaafar, and Nor Fadzilah Othman. "Temperature Distribution Analysis on Syngas Combustion in Microgas Turbine." Applied Mechanics and Materials 819 (January 2016): 282–86. http://dx.doi.org/10.4028/www.scientific.net/amm.819.282.
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Gas turbines are capable to utlize variety of fuel including natural gas, fuel oils and synthetic gas. It has environmental advantages and thus gas turbines are favourable in the power generating industries. The use of synthetic gas or syngas may reduce the CO2 and NOx emissions. The efficiency of syngas is comparable with natural gas. With the current constrain on the environmental issues, the use of syngas in gas turbines has been increasing. Despite its many advantages, the study on the combustion characteristics still remains a challenge, due to its variety fuel components. This paper aims to discuss the CFD analysis on the flame and flue gas temperature distribution in a full scale microgas turbine operating on syngas. Three cases were simulated with variety of natural gas concentration. A base case firing natural gas (100% methane) was first established using actual operation. Validation on the combustion model is made by comparing the flame temperature distribution of methane with reasonable accuracy. Simulation results with syngas show similar flame temperature distribution as natural gas combustion. The average temperature is much dependent on the composition of methane in syngas. The highest temperature given by syngas is made from the highest methane composiotion.
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Semakina, E. Yu, V. A. Chernikov, and V. Ch Khoang. "Experimental Aerodynamic Investigations of the 100-MW Two-Shaft Gas Turbine Unit Exhaust Duct." Thermal Engineering 66, no. 6 (May 31, 2019): 415–24. http://dx.doi.org/10.1134/s0040601519060089.
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Wilson, D. G. "Low-leakage and High-Flow Regenerators for Gas Turbine Engines." Proceedings of the Institution of Mechanical Engineers, Part A: Journal of Power and Energy 207, no. 3 (August 1993): 195–202. http://dx.doi.org/10.1243/pime_proc_1993_207_033_02.
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The preliminary analysis and development of two new forms of regenerative heat exchanger that seem to promise greatly improved performance characteristics is described. To reduce drastically the usually high leakage and high seal wear rates suffered by present rotary regenerators, discontinuous rotation of the matrix has been studied, with seals that clamp the matrix during the stationary periods. To enable the regenerative gas turbine cycle to be used at high powers, regenerators consisting of movable ceramic modules are being investigated. The potential applications of the discontinuous-rotation type are particularly to small lightweight gas turbine engines such as those for automotive applications and to helicopters and light turboprop aircraft. The modular regenerator is being studied in application to burning coal and biomass of gas turbine engines and to larger marine and stationary base-power engines with power outputs of up to (and possibly beyond) 100 MW.
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Langston, Lee S. "Plowing New Ground." Mechanical Engineering 131, no. 05 (May 1, 2009): 40–44. http://dx.doi.org/10.1115/1.2009-may-5.
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This article presents an overview of the gas turbine industry. The annual value of production provides the vital signs for the industry. Forecast International in Newtown, Connecticut, uses its computer models and extensive database to monitor value of production for both the aviation and the non-aviation gas turbine market. The largest segment in the industry is aviation—jet engines and turboprop engines for commercial and military manned aircraft—with $21.4 billion in production. While aviation is the largest market for gas turbines, the non-aviation segment is the broadest. General Electric’s new LMS100 gas turbine is one example firmly on the cutting edge. Introduced in 2005 and rated at 100 MW, the LMS100 is the first modern production electric power gas turbine to have an intercooler. The LMS100 is aimed at the mid-merit and daily cycling segments of the electrical market—the difficult-to-predict, must-be-ready-to-start electrical peak and intermediary power providers.
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El Hadik, A. A. "The Impact of Atmospheric Conditions on Gas Turbine Performance." Journal of Engineering for Gas Turbines and Power 112, no. 4 (October 1, 1990): 590–96. http://dx.doi.org/10.1115/1.2906210.
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In a hot summer climate, as in Kuwait and other Arabian Gulf countries, the performance of a gas turbine deteriorates drastically during the high-temperature hours (up to 60°C in Kuwait). Power demand is the highest at these times. This necessitates an increase in installed gas turbine capacities to balance this deterioration. Gas turbines users are becoming aware of this problem as they depend more on gas turbines to satisfy their power needs and process heat for desalination due to the recent technical and economical development of gas turbines. This paper is devoted to studying the impact of atmospheric conditions, such as ambient temperature, pressure, and relative humidity on gas turbine performance. The reason for considering air pressures different from standard atmospheric pressure at the compressor inlet is the variation of this pressure with altitude. The results of this study can be generalized to include the cases of flights at high altitudes. A fully interactive computer program based on the derived governing equations is developed. The effects of typical variations of atmospheric conditions on power output and efficiency are considered. These include ambient temperature (range from −20 to 60°C), altitude (range from zero to 2000 m above sea level), and relative humidity (range from zero to 100 percent). The thermal efficiency and specific net work of a gas turbine were calculated at different values of maximum turbine inlet temperature (TIT) and variable environmental conditions. The value of TIT is a design factor that depends on the material specifications and the fuel/air ratio. Typical operating values of TIT in modern gas turbines were chosen for this study: 1000, 1200, 1400, and 1600 K. Both partial and full loads were considered in the analysis. Finally the calculated results were compared with actual gas turbine data supplied by manufacturers.
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Sadig, Hussain, Shaharin Anwar Sulaiman, and Ibrahim Idris. "Exergy Analysis of a Micro-Gas Turbine Fueled with Syngas." Applied Mechanics and Materials 465-466 (December 2013): 142–48. http://dx.doi.org/10.4028/www.scientific.net/amm.465-466.142.
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A theoretical exergetic analysis of a small-scale gas-turbine system fueled with two different syngas fuels is discussed in this paper. For carrying out the analysis, a micro-gas turbine system with a thermal heat input of 50 kW was simulated using ASPEN plus simulator. Quantitative exergy balance was applied for each component in the cycle. The effects of excess air, ambient air temperature, and heat input on the exergy destruction and exergetic efficiency for each component were evaluated and compared with those resulted from fueling the system with liquefied petroleum gas (LPG). For 50 kW heat input and 50% excess air, the total exergy destruction for LPG, Syngas1, and Syngas2 were found to be 17.3, 14.3, and 13.6 kW, respectively. It was found that increasing the excess air ratio to 100% increased the combustion chamber exergetic efficiency by 8%-10% but it reduced the exergetic efficiency of other components. The same trend was observed when tested ambient air temperature. The results also showed a reduction in the combustion chamber exergetic efficiency by 2%-4% when a 20% heat input increase was applied.
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Jones, A. C. "Design and Test of a Small, High Pressure Ratio Radial Turbine." Journal of Turbomachinery 118, no. 2 (April 1, 1996): 362–70. http://dx.doi.org/10.1115/1.2836651.
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This paper describes the aerodynamic design and rig test of a radial inflow turbine having a rotor tip diameter of 4.58 inches. The single-stage turbine was designed for use in the Sundstrand Power Systems (SPS) T-100 Multipurpose Small Power Unit (MPSPU). The T-100 is a small, single-shaft, simple-cycle gas turbine engine intended for airborne, vehicular, and ground-based auxiliary power application. Nominal power output of the engine is 50 hp, with growth capability to 100 hp with minimal modification. Aggressive specific fuel consumption goals for the engine led to a demanding turbine efficiency target of 87 percent total to static, referred to exhaust diffuser exit, at an expansion ratio of 5.7:1 and a flow rate of 0.73 lb/s. Details of the design approach are given, together with test results from the turbodrive rig. The results include overall stage mapping and rotor exit surveys.
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Kalina, Jacek. "Fossil fuel savings, carbon emission reduction and economic attractiveness of medium-scale integrated biomass gasification combined cycle cogeneration plants." Thermal Science 16, no. 3 (2012): 827–48. http://dx.doi.org/10.2298/tsci120126124k.
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The paper theoretically investigates the system made up of fluidized bed gasifier, SGT-100 gas turbine and bottoming steam cycle. Different configurations of the combined cycle plant are examined. A comparison is made between systems with producer gas (PG) and natural gas (NG) fired turbine. Supplementary firing of the PG in a heat recovery steam generator is also taken into account. The performance of the gas turbine is investigated using in-house built Engineering Equation Solver model. Steam cycle is modeled using GateCycleTM simulation software. The results are compared in terms of electric energy generation efficiency, CO2 emission and fossil fuel energy savings. Finally there is performed an economic analysis of a sample project. The results show relatively good performance in the both alternative configurations at different rates of supplementary firing. Furthermore, positive values of economic indices were obtained.
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Kumakura, H., M. Sasaki, D. Suzuki, and H. Ichikawa. "Development of a Low-Emission Combustor for a 100-kW Automotive Ceramic Gas Turbine (II)." Journal of Engineering for Gas Turbines and Power 118, no. 1 (January 1, 1996): 167–72. http://dx.doi.org/10.1115/1.2816534.
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Performance tests were conducted on a low-emission combustor, which has a pre-vaporization–premixing lean combustion system and is designed for a 100 kW automotive ceramic gas turbine. The results of steady-state combustion tests performed at an inlet temperature of 1000–1200 K and pressure of 0.1–0.34 MPa indicate that the combustor would meet Japan’s emission standards for gasoline engine passenger cars without using an aftertreatment system. Flashback was suppressed by controlling the mixture velocity and air ratios. Strength tests conducted on rings and bars cut from the actual ceramic parts indicate that the combustor has nearly the same level of strength as standard test specimens.
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Sato, H., M. Mori, and T. Nakamura. "Development of a Dry Ultra-Low NOx Double Swirler Staged Gas Turbine Combustor." Journal of Engineering for Gas Turbines and Power 120, no. 1 (January 1, 1998): 41–47. http://dx.doi.org/10.1115/1.2818086.
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This paper describes the development of an ultra-low NOx gas turbine combustor for cogeneration systems. The combustor, called a double swirler staged combustor, utilizes three-staged premixed combustion for low NOx emission. The unique feature of the combustor is its tertiary premix nozzles located downstream of the double swirler premixing nozzles around the combustor liner. Engine output is controlled by simply varying the fuel gas flow, and therefore employs no complex variable geometries for airflow control. Atmospheric combustion tests have demonstrated the superior performance of the combustor. NOx level is maintained at less than 3 ppm (O2 = 15 percent) over the range of engine output between 50 and 100 percent. Assuming the general relationship that NOx emission is proportional to the square root of operating pressure, the NOx level is estimated at less than 9 ppm (O2 = 15 percent) at the actual pressure of 0.91 MPa (abs.). Atmospheric tests have also shown high combustion efficiency; more than 99.9 percent over the range of engine output between 60 and 100 percent. Emissions of CO and UHC are maintained at 0 and 1 ppm (O2 = 15 percent), respectively, at the full engine load.
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Kozak, Nikita, Fei Xu, Manoj R. Rajanna, Luis Bravo, Muthuvel Murugan, Anindya Ghoshal, Yuri Bazilevs, and Ming-Chen Hsu. "High-Fidelity Finite Element Modeling and Analysis of Adaptive Gas Turbine Stator-Rotor Flow Interaction at Off-Design Conditions." Journal of Mechanics 36, no. 5 (August 10, 2020): 595–606. http://dx.doi.org/10.1017/jmech.2020.28.
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ABSTRACTThe objective of this work is to computationally investigate the impact of an incidence-tolerant rotor blade concept on gas turbine engine performance under off-design conditions. When a gas turbine operates at an off-design condition such as hover flight or takeoff, large-scale flow separation can occur around turbine blades, which causes performance degradation, excessive noise, and critical loss of operability. To alleviate this shortcoming, a novel concept which articulates the rotating turbine blades simultaneous with the stator vanes is explored. We use a finite-element-based moving-domain computational fluid dynamics (CFD) framework to model a single high-pressure turbine stage. The rotor speeds investigated range from 100% down to 50% of the designed condition of 44,700 rpm. This study explores the limits of rotor blade articulation angles and determines the maximal performance benefits in terms of turbine output power and adiabatic efficiency. The results show articulating rotor blades can achieve an efficiency gain of 10% at off-design conditions thereby providing critical leap-ahead design capabilities for the U.S. Army Future Vertical Lift (FVL) program.
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Fujii, T., Y. Ozawa, S. Kikumoto, M. Sato, Y. Yuasa, and H. Inoue. "High Pressure Test Results of a Catalytic Combustor for Gas Turbine." Journal of Engineering for Gas Turbines and Power 120, no. 3 (July 1, 1998): 509–13. http://dx.doi.org/10.1115/1.2818174.
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Recently, the use of gas turbine systems, such as combined cycle and cogeneration systems, has gradually increased in the world. But even when a clean fuel such as LNG (liquefied natural gas) is used, thermal NOx is generated in the high temperature gas turbine combustion process. The NOx emission from gas turbines is controlled through selective catalytic reduction processes (SCR) in the Japanese electric industry. If catalytic combustion could be applied to the combustor of the gas turbine, it is expected to lower NOx emission more economically. Under such high temperature and high pressure conditions, as in the gas turbine, however, the durability of the catalyst is still insufficient. So it prevents the realization of a high temperature catalytic combustor. To overcome this difficulty, a catalytic combustor combined with premixed combustion for a 1300°C class gas turbine was developed. In this method, catalyst temperature is kept below 1000°C, and a lean premixed gas is injected into the catalytic combustion gas. As a result, the load on the catalyst is reduced and it is possible to prevent the catalyst deactivation. After a preliminary atmospheric test, the design of the combustort was modified and a high pressure combustion test was conducted. As a result, it was confirmed that NOx emission was below 10 ppm (at 16 percent O2) at a combustor outlet gas temperature of 1300°C and that the combustion efficiency was almost 100 percent. This paper presents the design features and test results of the combustor.
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Serbin, Serhiy, Badri Diasamidze, Viktor Gorbov, and Jerzy Kowalski. "Investigations of the Emission Characteristics of a Dual-Fuel Gas Turbine Combustion Chamber Operating Simultaneously on Liquid and Gaseous Fuels." Polish Maritime Research 28, no. 2 (June 1, 2021): 85–95. http://dx.doi.org/10.2478/pomr-2021-0025.
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Abstract This study is dedicated to investigations of the working process in a dual-fuel low-emission combustion chamber for a floating vessel’s gas turbine. As the object of the research, a low-emission gas turbine combustion chamber with partial premixing of fuel and air inside the outer and inner radial-axial swirls was chosen. The method of the research is based on the numerical solution of the system of differential equations which represent the physical process of mass and energy conservation and transformations and species transport for a multi-component chemically reactive turbulent system, considering nitrogen oxides formation and a discrete ordinates model of radiation. The chemistry kinetics is presented by the 6-step mechanism of combustion. Seven fuel supply operating modes, varying from 100% gaseous fuel to 100% liquid fuel, have been analysed. This analysis has revealed the possibility of the application of computational fluid dynamics for problems of dual-fuel combustion chambers for the design of a floating vessel’s gas turbine. Moreover, the study has shown the possibility of working in different transitional gaseous and liquid fuel supply modes, as they satisfy modern ecological requirements. The dependencies of the averaged temperature, NO, and CO concentrations along the length of the low-emission gas turbine combustion chamber for different cases of fuel supply are presented. Depending on the different operating modes, the calculated emission of nitrogen oxides NO and carbon monoxide CO at the outlet cross-section of a flame tube are different, but, they lie in the ranges of 31‒50 and 23‒24 mg/nm3 on the peak of 100% liquid fuel supply mode. At operating modes where a gaseous fuel supply prevails, nitrogen oxide NO and carbon monoxide CO emissions lie in the ranges of 1.2‒4.0 and 0.04‒18 mg/nm3 respectively.
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Loughney, S., J. Wang, and DB Matellini. "Utilising Bayesian networks to demonstrate the potential consequences of a fuel gas release from an offshore gas-driven turbine." Proceedings of the Institution of Mechanical Engineers, Part M: Journal of Engineering for the Maritime Environment 233, no. 4 (December 7, 2018): 1177–97. http://dx.doi.org/10.1177/1475090218816218.
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This research proposes the application of Bayesian networks in conducting quantitative risk assessment of the integrity of an offshore gas driven turbine, used for electrical power generation. The focus of the research is centred on the potential release of fuel gas from a turbine and the potential consequences that follow the said release, such as fire, explosion and damage to equipment within the electrical generation module. The Bayesian network demonstrates the interactions of potential initial events and failures, hazards, barriers and consequences involved in a fuel gas release. This model allows for quantitative analysis to demonstrate partial verification of the model. The verification of the model is demonstrated in a series of test cases and through sensitivity analysis. Test case 1 demonstrates the effects of individual and combined control system failures within the fuel gas release model; 2 demonstrates the effects of the 100% probability of a gas release on the Bayesian network model, along with the effect of the gas detection system not functioning; and 3 demonstrates the effects of inserting evidence as a consequence and observing the effects on prior nodes.
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Larson, Eric D., Stefano Consonni, and Thomas G. Kreutz. "Preliminary Economics of Black Liquor Gasifier/Gas Turbine Cogeneration at Pulp and Paper Mills." Journal of Engineering for Gas Turbines and Power 122, no. 2 (January 3, 2000): 255–61. http://dx.doi.org/10.1115/1.483203.
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Black liquor, the lignin-rich byproduct of kraft pulp production, is burned in boiler/steam turbine cogeneration systems at pulp mills today to provide heat and power for onsite use. Black liquor gasification technologies under development would enable this fuel to be used in gas turbines. This paper reports preliminary economics of 100-MWe scale integrated black-liquor gasifier/combined cycles using alternative commercially proposed gasifier designs. The economics are based on detailed full-load performance modeling and on capital, operating and maintenance costs developed in collaboration with engineers at Bechtel Corporation and Stone & Webster Engineering. Comparisons with conventional boiler/steam turbine systems are included. [S0742-4795(00)00402-6]
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Martins, Rui F., Carlos M. Branco, António M. Gonçalves-Coelho, and Edgar C. Gomes. "Metallurgical Study of a AISI 316L Stainless Steel Used in a Gas Turbine Exhaust System." Materials Science Forum 514-516 (May 2006): 1521–25. http://dx.doi.org/10.4028/www.scientific.net/msf.514-516.1521.
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Several high temperature fatigue and possibly creep-fatigue cracks have nucleated and propagated through the 3.7 mm wall thickness of a gas turbine exhaust system of a navy combat ship made of a grade type AISI 316L annealed stainless steel. The main cracks propagated near some welded joints, where the measured working temperature was approximately equal to 350°C (Fig.1). The paper presents tensile, fatigue and creep data obtained from experimental tests that were performed in several test specimens obtained from steel plates used in-service. Results of optical microscopy for the microstructure of the material and analysis of the fracture surfaces carried out with the SEM have identified the failure mechanisms at test temperatures. The paper also presents microhardness and grain size measurements carried out together with microstructural observations in the SEM. A research work to investigate carbide precipitation in virgin thin sheet specimens, as used in these exhaust tubes, was also performed and it is presented. The influence of stages time (100, 200, 100+100 and 4x50 hours) and of thermal exposure temperatures (500 and 550°C) was assessed to compare the metallurgical properties of the material. Finally, the paper shortly analyses other materials that could replace the used one.
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Yan, Yingwen, Yunpeng Liu, Liang Huang, and Jinghua Li. "Effects of Inlet Parameters on Combustion Performance in Gas Turbine Combustor." International Journal of Turbo & Jet-Engines 35, no. 4 (December 19, 2018): 339–50. http://dx.doi.org/10.1515/tjj-2016-0058.
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Abstract The effects of different inlet parameters such as inlet temperature and pressure on combustion performance in a single-head combustor were experimentally investigated in this study. The combustion efficiency, total pressure loss, and CO and NO emissions at the outlet of a single-head rectangular combustor with different types of swirlers were separately measured. The experimental results showed that the inlet parameters had obvious effects on the combustion performance, with critical values of 600 K for the inlet temperature and 3.5 bar for the inlet pressure. The combustion efficiency noticeably increased with an increase in the inlet pressure or temperature below these values; however, when either of the inlet parameters was above the critical value, the combustion efficiency was approximately 100 %; that is, the combustion efficiency changed little with an increase in inlet temperate or pressure. When the inlet temperature or pressure increased, NO emission increased but CO emission decreased. By fitting curves to analyze the experimental data, the empirical relationships between the emissions and the inlet temperature were observed to be $CO\; \propto \;{e^{ - T}}, NO\; \propto \;{e^T}$, and those between the emissions and the inlet pressure were $CO\, \propto \,{e^{a + bP + c{P^2}}}, NO\, \propto \,{e^P}$. The total pressure loss increased with the inlet temperature.
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Bonolo de Campos, Gustavo, Cleverson Bringhenti, Alberto Traverso, and Jesuino Takachi Tomita. "A Review on Combining Micro Gas Turbines with Organic Rankine Cycles." E3S Web of Conferences 113 (2019): 03007. http://dx.doi.org/10.1051/e3sconf/201911303007.
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Current energy conversion machines such as the micro gas turbine can be improved by harvesting the low-grade energy of the exhaust. A prominent option for such is the organic Rankine cycle due to its relatively efficient and reliable design. This manuscript presents a review on the subject and is the first step toward the design of an organic Rankine cycle bottoming a 100 kWe recuperated gas turbine. After introducing and covering the historical development of the technology, appropriate guidelines for defining the cycle arrangement and selecting the fluid are presented. At last, the viability of the cycle is assessed by assuming an appropriate efficiency value and general cost functions. The organic Rankine is expected to generate an additional 16.6 kWe of power, increasing the electrical efficiency from 30 to 35%. However, the capital cost increase was estimated in 48%.
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Ramadhan, Mohammad, Abdulhameed Hussain, and Dina Behbehani. "The Prospect of Solar Energy in the Development of Power Stations in the State of Kuwait." Journal of Renewable Energy 2013 (2013): 1–6. http://dx.doi.org/10.1155/2013/374265.
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Over the years, the production capacity for power generation has not been able to keep pace with the surge in electricity demand in the oil-rich State of Kuwait. To expand its power generation capacity, Kuwait's strategic energy plans focus on constructing gas turbine and fuel oil stations. This paper aimed to evaluate the prospect of photovoltaic solar energy (PV) in generating electricity as an alternative to decrease dependency on combined cycle gas turbine (CCGT) power stations. It applies the LCOE framework to evaluate the economic feasibility of installing a 100 MW PV and CCGT power stations in Kuwait. The results indicate that under the assumption of 5% interest rate, the estimated LCOE of PV station ($0.19/kWh) is unfeasible in comparison to the generation cost of gas turbine station ($0.11/kWh). However, the analysis has emphasized that evaluation of future electricity generation plans must not be limited to the LCOE criteria and should incorporate the following factors: the effect of natural gas supply constraints on the production of gas turbine plants, the environmental concerns of CO2emissions, the peak load demand, and the domestic energy balance mix. The paper concludes that once these factors are addressed properly, the prospect of PV power stations becomes relatively feasible.
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Lee, An Sung, and Alexandre F. Vedichtchev. "LP compressor blade vibration characteristics at starting conditions of a 100 MW heavy-duty gas turbine." KSME International Journal 18, no. 6 (June 2004): 895–903. http://dx.doi.org/10.1007/bf02990861.
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Hung, W. S. Y. "Carbon Monoxide Emissions From Gas Turbines as Influenced by Ambient Temperature and Turbine Load." Journal of Engineering for Gas Turbines and Power 115, no. 3 (July 1, 1993): 588–93. http://dx.doi.org/10.1115/1.2906747.
Full textAbstract:
The emissions of carbon monoxide (CO) from gas turbines are typically below 100 ppmvd at 15 percent O2 at design full-load operating conditions. The use of water/ steam to reduce NOx emissions from gas turbines results in an increase in CO emissions from gas turbines. This is particularly true when increased rates of water/ steam injection are used to meet stringent NOx limits. Regulations limiting CO emissions from stationary gas turbines were first initiated in the late 1980s by the Federal Republic of Germany and the state of New Jersey in the United States. Since these regulations are silent on ambient and load corrections, these CO limits could be the limiting factor in the current development of dry low-NOx combustion systems by gas turbine manufacturers. In addition, since manufacturers are usually quite specific regarding the conditions for CO guarantees, a conflict for the gas turbine user, who is responsible for the permit application, is readily apparent. This paper attempts to characterize the CO emissions from gas turbines as a function of ambient temperature and turbine load. An ambient temperature correction equation for CO emissions, based on previous work, is presented. The intent is to provide more extensive information on CO emissions such that better defined CO limits can be adopted. Ultimately, this should help the combustion design engineers in developing improved dry low-emissions combustion systems for the gas turbine industry.