Journal articles: 'Aerospace gas turbines'

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Asgari, Hamid, Mohsen Fathi Jegarkandi, XiaoQi Chen, and Raazesh Sainudiin. "Design of conventional and neural network based controllers for a single-shaft gas turbine." Aircraft Engineering and Aerospace Technology 89, no. 1 (January 3, 2017): 52–65. http://dx.doi.org/10.1108/aeat-11-2014-0187.

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Purpose The purpose of this paper is to develop and compare conventional and neural network-based controllers for gas turbines. Design/methodology/approach Design of two different controllers is considered. These controllers consist of a NARMA-L2 which is an artificial neural network-based nonlinear autoregressive moving average (NARMA) controller with feedback linearization, and a conventional proportional-integrator-derivative (PID) controller for a low-power aero gas turbine. They are briefly described and their parameters are adjusted and tuned in Simulink-MATLAB environment according to the requirement of the gas turbine system and the control objectives. For this purpose, Simulink and neural network-based modelling is used. Performances of the controllers are explored and compared on the base of design criteria and performance indices. Findings It is shown that NARMA-L2, as a neural network-based controller, has a superior performance to PID controller. Practical implications This study aims at using artificial intelligence in gas turbine control systems. Originality/value This paper provides a novel methodology for control of gas turbines.

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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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Fersini, Maurizio, R. Bianco, L. De Lorenzis, Antonio Licciulli, G. Pasquero, and G. Zanon. "Thermo-Structural Analysis of Ceramic Vanes for Gas Turbines." Advances in Science and Technology 45 (October 2006): 1759–64. http://dx.doi.org/10.4028/www.scientific.net/ast.45.1759.

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Advanced structural ceramics such as Hot Pressed Silicon Nitride (HPSN) and Reaction Bonded Silicon Carbide (RBSC), thanks to their low density (3.1 ÷ 3.4 gr/cm3) and to their thermostructural properties, are interesting candidates for aerospace applications. This research investigates the feasibility of employing such monolithic advanced ceramics for the production of turbine vanes for aerospace applications, by means of a finite element analysis. A parametric study is performed to analyse the influence of the coefficient of thermal expansion, the specific heat, the thermal conductivity, and the Weibull modulus on structural stability, heat transfer properties and thermomechanical stresses under take-off and flying conditions. A nodal point that is evidenced is the high intensity of thermal stresses on the vane, both on steady state and in transient conditions. In order to reduce such stresses various simulations have been carried out varying geometrical parameters such as the wall thickness. Several open questions are evidenced and guidelines are drawn for the design and production of ceramic vanes for gas turbines.

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Bhargava, R., M. Bianchi, A. Peretto, and P. R. Spina. "A Feasibility Study of Existing Gas Turbines for Recuperated, Intercooled, and Reheat Cycle." Journal of Engineering for Gas Turbines and Power 126, no. 3 (July 1, 2004): 531–44. http://dx.doi.org/10.1115/1.1707033.

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In the present paper, a comprehensive and simple in application design methodology to obtain a gas turbine working on recuperated, intercooled, and reheat cycle utilizing existing gas turbines is presented. Applications of the proposed design steps have been implemented on the three existing gas turbines with wide ranging design complexities. The results of evaluated aerothermodynamic performance for these existing gas turbines with the proposed modifications are presented and compared in this paper. Sample calculations of the analysis procedures discussed, including stage-by-stage analysis of the compressor and turbine sections of the modified gas turbines, have been also included. All the three modified gas turbines were found to have higher performance, with cycle efficiency increase of 9% to 26%, in comparison to their original values.

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Fatsis, Antonios. "Performance Enhancement of One and Two-Shaft Industrial Turboshaft Engines Topped With Wave Rotors." International Journal of Turbo & Jet-Engines 35, no. 2 (May 25, 2018): 137–47. http://dx.doi.org/10.1515/tjj-2016-0040.

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Abstract Wave rotors are rotating equipment designed to exchange energy between high and low enthalpy fluids by means of unsteady pressure waves. In turbomachinery, they can be used as topping devices to gas turbines aiming to improve performance. The integration of a wave rotor into a ground power unit is far more attractive than into an aeronautical application, since it is not accompanied by any inconvenience concerning the over-weight and extra dimensioning. Two are the most common types of ground industrial gas turbines: The one-shaft and the two-shaft engines. Cycle analysis for both types of gas turbine engines topped with a four-port wave rotor is calculated and their performance is compared to the performance of the baseline engine accordingly. It is concluded that important benefits are obtained in terms of specific work and specific fuel consumption, especially compared to baseline engines with low compressor pressure ratio and low turbine inlet temperature.

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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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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.

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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.

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Bianchi, M., G. Negri di Montenegro, A. Peretto, and P. R. Spina. "A Feasibility Study of Inverted Brayton Cycle for Gas Turbine Repowering." Journal of Engineering for Gas Turbines and Power 127, no. 3 (June 24, 2005): 599–605. http://dx.doi.org/10.1115/1.1765121.

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In the paper a feasibility study of inverted Brayton cycle (IBC) engines, for the repowering of existing gas turbines, is presented. The following main phases have been carried out: (i) identification of the more suitable gas turbines to be repowered by means of an IBC engine; (ii) designing of the IBC components. Once the IBC engines for the candidate gas turbines were designed, an analysis has been developed to check the possibility to match these engines with other gas turbines, similar to those for which the IBC engines have been designed. In all the analyzed cases the evaluated performance result only slightly worse than that obtainable by repowering the same gas turbine with IBC engines ad hoc designed.

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Bogomolov, E. N., and P. V. Kashcheeva. "Thermodynamic features of aircraft diagonal gas turbines." Russian Aeronautics (Iz VUZ) 52, no. 2 (June 2009): 250–54. http://dx.doi.org/10.3103/s1068799809020196.

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10

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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Bhargava, R., and C. B. Meher-Homji. "Parametric Analysis of Existing Gas Turbines With Inlet Evaporative and Overspray Fogging." Journal of Engineering for Gas Turbines and Power 127, no. 1 (January 1, 2005): 145–58. http://dx.doi.org/10.1115/1.1712980.

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With deregulation in the power generation market and a need for flexibility in terms of power augmentation during the periods of high electricity demand, power plant operators all over the world are exploring means to augment power from both the existing and new gas turbines. An approach becoming increasingly popular is that of the high pressure inlet fogging. In this paper, the results of a comprehensive parametric analysis on the effects of inlet fogging on a wide range of existing gas turbines are presented. Both evaporative and overspray fogging conditions have been analyzed. The results show that the performance parameters indicative of inlet fogging effects have a definitive correlation with the key gas turbine design parameters. In addition, this study indicates that the aeroderivative gas turbines, in comparison to the heavy-duty industrial machines, have higher performance improvement due to inlet fogging effects. Plausible reasons for the observed trends are discussed. This paper represents the first systematic study on the effects of inlet fogging for a large number (a total of 67) of gas turbines available from the major gas turbine manufacturers.

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Bogdanov, V. I. "Concepts of Gas Turbine Engine Improvement Through the Use of Choked-Flow Turbines." Russian Aeronautics 61, no. 2 (April 2018): 244–51. http://dx.doi.org/10.3103/s1068799818020137.

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13

Larson, E. D., and R. H. Williams. "Biomass-Gasifier Steam-Injected Gas Turbine Cogeneration." Journal of Engineering for Gas Turbines and Power 112, no. 2 (April 1, 1990): 157–63. http://dx.doi.org/10.1115/1.2906155.

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Steam injection for power and efficiency augmentation in aeroderivative gas turbines is now commercially established for natural gas-fired cogeneration. Steam-injected gas turbines fired with coal and biomass are being developed. In terms of efficiency, capital cost, and commercial viability, the most promising way to fuel steam-injected gas turbines with biomass is via the biomass-integrated gasifier/steam-injected gas turbine (BIG/STIG). The R&D effort required to commercialize the BIG/STIG is modest because it can build on extensive previous coal-integrated gasifier/gas turbine development efforts. An economic analysis of BIG/STIG cogeneration is presented here for cane sugar factories, where sugar cane residues would be the fuel. A BIG/STIG investment would be attractive for sugar producers, who could sell large quantities of electricity, or for the local electric utility, as a low-cost generating option. Worldwide, the cane sugar industry could support some 50,000 MW of BIG/STIG capacity, and there are many potential applications in the forest products and other biomass-based industries.

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Cooke, D. H., and W. D. Parizot. "Cogenerative, Direct Exhaust Integration of Gas Turbines in Ethylene Production." Journal of Engineering for Gas Turbines and Power 113, no. 2 (April 1, 1991): 212–20. http://dx.doi.org/10.1115/1.2906547.

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Within the past few years, gas turbines have been integrated into several new world-class ethylene production plants, for the first time using the exhaust as a source of preheated combustible oxygen for the cracking furnaces. The economic inducements and technical impact of such integration on the process are discussed. The general ethylene cracking and recovery process is described, and the various ways of integrating gas turbines are compared, culminating in the current leading designs. Means of providing ambient air backup to protect furnace operation from gas turbine trips are discussed. Furnace group sizing and oxygen demand for the major feedstocks, including naphtha and ethane/propane, are compared with the current range of oxygen and power available from single and dual gas turbines on the world market. Methods of partial integration, where gas turbine integration of the entire ethylene plant would produce more power than can be economically utilized or consume more premium fuel than available, are discussed. Fuel savings relative to ambient air operation are parametrized with percent exhaust oxygen and exhaust temperature. Aeroderivative and industrial gas turbine types are compared. Comparative economics with another means of gas turbine cogeneration, that of auxiliary boiler replacement with a combined cycle in a central utility, are presented.

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Bruce, C. J., and R. A. Cartwright. "Marine Gas Turbine Evaluation and Research at the Admiralty Test House, RAE Pyestock." Journal of Engineering for Gas Turbines and Power 114, no. 2 (April 1, 1992): 169–73. http://dx.doi.org/10.1115/1.2906566.

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The Admiralty Test House (ATH) at the Royal Aerospace Establishment Pyestock has provided test bed facilities for evaluation of marine gas turbines and ancillary equipments for Royal Naval use since 1952. While the ATH is presently undergoing an extensive refurbishment program in preparation for trials of the Rolls-Royce 20MW Spey SM1C, research continues on a number of innovative gas turbine condition monitoring techniques. This paper presents a brief history of the Marine Gas Turbine Section and describes the facilities of the ATH following major refurbishment. The capabilities of the steady-state and transient data gathering facilities are outlined, together with the automated engine and test control systems, which provide cost-effective engine evaluation in both endurance and minor equipment trials.

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Becker, B., and B. Schetter. "Gas Turbines Above 150 MW for Integrated Coal Gasification Combined Cycles (IGCC)." Journal of Engineering for Gas Turbines and Power 114, no. 4 (October 1, 1992): 660–64. http://dx.doi.org/10.1115/1.2906639.

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Commercial IGCC power plants need gas turbines with high efficiency and high power output in order to reduce specific installation costs and fuel consumption. Therefore the well-proven 154 MW V94.2 and the new 211 MW V94.3 high-temperature gas turbines are well suited for this kind of application. A high degree of integration of the gas turbine, steam turbine, oxygen production, gasifier, and raw gas heat recovery improves the cycle efficiency. The air use for oxygen production is taken from the gas turbine compressor. The N2 fraction is recompressed and mixed with the cleaned gas prior to combustion. Both features require modifications of the gas turbine casing and the burners. Newly designed burners using the coal gas with its very low heating value and a mixture of natural gas and steam as a second fuel are developed for low NOx and CO emissions. These special design features are described and burner test results presented.

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Parks, W. P., R. R. Ramey, D. C. Rawlins, J. R. Price, and M. Van Roode. "Potential Applications of Structural Ceramic Composites in Gas Turbines." Journal of Engineering for Gas Turbines and Power 113, no. 4 (October 1, 1991): 628–34. http://dx.doi.org/10.1115/1.2906287.

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A Babcock and Wilcox-Solar Turbines Team has completed a program to assess the potential for structural ceramic composites in turbines for direct coal-fired or coal gasification environments. A review is made of the existing processes in direct coal firing, pressurized fluid bed combustors, and coal gasification combined cycle systems. Material requirements in these areas were also discussed. The program examined state-of-the-art ceramic composite materials. Utilization of ceramic composites in the turbine rotor blades and nozzle vanes would provide the most benefit. A research program designed to introduce ceramic composite components to these turbines was recommended.

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Hoshino, A., T. Sugimoto, T. Tatsumi, and Y. Nakagawa. "Development of a 30PS Class Small Gas Turbine and Its Power-Up Version." Journal of Engineering for Gas Turbines and Power 111, no. 2 (April 1, 1989): 225–31. http://dx.doi.org/10.1115/1.3240240.

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Due to the recent popularity of small and medium-sized industrial gas turbines in many fields, gas turbines below 100 SHP have been employed as prime movers, a power range traditionally reserved for diesel and gasoline engines. Generally speaking, however, small gas turbines have many design difficulties in thermal efficiency, high rotational speed, compact auxiliary equipment, etc., derived from limitations of their dimensions. Small gas turbines S5A-01 and S5B-01, which have 32 PS output power at standard conditions, have been developed and are being produced. Presently, a 30 percent growth rated power producer for S5A-02 and S5B-02 gas turbines is under development. These engines’ configurations are as follows: single-stage centrifugal compressor; single-stage radial turbine; single can combustor; hybrid fuel nozzle with pressure atomizer and airblast atomizer; fuel control valve with pulse width modulation system; electric motor drive fuel pump. In this paper, the authors describe the design features and development history of the base engine and the experimental results with the growth rated version.

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Rodgers, C. "Impingement Starting and Power Boosting of Small Gas Turbines." Journal of Engineering for Gas Turbines and Power 107, no. 4 (October 1, 1985): 821–27. http://dx.doi.org/10.1115/1.3239817.

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The technology of high-pressure air or hot-gas impingement from stationary shroud supplementary nozzles onto radial outflow compressors and radial inflow turbines to permit rapid gas turbine starting or power boosting is discussed. Data are presented on the equivalent turbine component performance for convergent/divergent shroud impingement nozzles, which reveal the sensitivity of nozzle velocity coefficient with Mach number and turbine efficiency with impingement nozzle admission arc. Compressor and turbine matching is addressed in the transient turbine start mode with the possibility of operating these components in braking or reverse flow regimes when impingement flow rates exceed design.

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Liao, Zengbu, Jian Wang, Jinxin Liu, Jia Geng, Ming Li, Xuefeng Chen, and Zhiping Song. "Uncertainties in gas-path diagnosis of gas turbines: Representation and impact analysis." Aerospace Science and Technology 113 (June 2021): 106724. http://dx.doi.org/10.1016/j.ast.2021.106724.

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Kyprianidis, K. G., V. Sethi, S. O. T. Ogaji, P. Pilidis, R. Singh, and A. I. Kalfas. "Uncertainty in gas turbine thermo-fluid modelling and its impact on performance calculations and emissions predictions at aircraft system level." Proceedings of the Institution of Mechanical Engineers, Part G: Journal of Aerospace Engineering 226, no. 2 (November 29, 2011): 163–81. http://dx.doi.org/10.1177/0954410011406664.

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In this article, various aspects of thermo-fluid modelling for gas turbines are described and the impact on performance calculations and emissions predictions at aircraft system level is assessed. Accurate and reliable fluid modelling is essential for any gas turbine performance simulation software as it provides a robust foundation for building advanced multi-disciplinary modelling capabilities. Caloric properties for generic and semi-generic gas turbine performance simulation codes can be calculated at various levels of fidelity; selection of the fidelity level is dependent upon the objectives of the simulation and execution time constraints. However, rigorous fluid modelling may not necessarily improve performance simulation accuracy unless all modelling assumptions and sources of uncertainty are aligned to the same level. A comprehensive analysis of thermo-fluid modelling for gas turbines is presented, and the fluid models developed are discussed in detail. Common technical models, used for calculating caloric properties, are compared while typical assumptions made in fluid modelling, and the uncertainties induced, are examined. Several analyses, which demonstrate the effects of composition, temperature, and pressure on caloric properties of working media for gas turbines, are presented. The working media examined include dry air and combustion products for various fuels and H/C ratios. The uncertainty induced in calculations by (a) using common technical models for evaluating fluid caloric properties and (b) ignoring dissociation effects is examined at three different levels: (i) component level, (ii) engine level, and (iii) aircraft system level. An attempt is made to shed light on the trade-off between improving the accuracy of a fluid model and the accuracy of a multi-disciplinary simulation at aircraft system level, against computational time penalties. The validity of the ideal gas assumption for future turbofan engines and novel propulsion cycles is discussed. The results obtained demonstrate that accurate modelling of the working fluid is essential, especially for assessing novel and/or aggressive cycles at aircraft system level. Where radical design space exploration is concerned, improving the accuracy of the fluid model will need to be carefully balanced with the computational time penalties involved.

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Fukuizumi, Y., J. Masada, V. Kallianpur, and Y. Iwasaki. "Application of “H Gas Turbine” Design Technology to Increase Thermal Efficiency and Output Capability of the Mitsubishi M701G2 Gas Turbine." Journal of Engineering for Gas Turbines and Power 127, no. 2 (April 1, 2005): 369–74. http://dx.doi.org/10.1115/1.1850490.

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Mitsubishi completed design development and verification load testing of a steam-cooled M501H gas turbine at a combined cycle power plant at Takasago, Japan in 2001. Several advanced technologies were specifically developed in addition to the steam-cooled components consisting of the combustor, turbine blades, vanes, and the rotor. Some of the other key technologies consisted of an advanced compressor with a pressure ratio of 25:1, active clearance control, and advanced seal technology. Prior to the M501H, Mitsubishi introduced cooling-steam in “G series” gas turbines in 1997 to cool combustor liners. Recently, some of the advanced design technologies from the M501H gas turbine were applied to the G series gas turbine resulting in significant improvement in output and thermal efficiency. A noteworthy aspect of the technology transfer is that the upgraded G series M701G2 gas turbine has an almost equivalent output and thermal efficiency as H class gas turbines while continuing to rely on conventional air cooling of turbine blades and vanes, and time-proven materials from industrial gas turbine experience. In this paper we describe the key design features of the M701G2 gas turbine that make this possible such as the advanced 21:1 compressor with 14 stages, an advanced premix DLN combustor, etc., as well as shop load test results that were completed in 2002 at Mitsubishi’s in-house facility.

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Khalid, A. H., K. Kontis, and H.-Z. Behtash. "Phosphor thermometry in gas turbines: Consideration factors." Proceedings of the Institution of Mechanical Engineers, Part G: Journal of Aerospace Engineering 224, no. 7 (July 2010): 745–55. http://dx.doi.org/10.1243/09544100jaero560.

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Rice, I. G. "Thermodynamic Evaluation of Gas Turbine Cogeneration Cycles: Part I—Heat Balance Method Analysis." Journal of Engineering for Gas Turbines and Power 109, no. 1 (January 1, 1987): 1–7. http://dx.doi.org/10.1115/1.3240001.

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This paper presents a heat balance method of evaluating various open-cycle gas turbines and heat recovery systems based on the first law of thermodynamics. A useful graphic solution is presented that can be readily applied to various gas turbine cogeneration configurations. An analysis of seven commercially available gas turbines is made showing the effect of pressure ratio, exhaust temperature, intercooling, regeneration, and turbine rotor inlet temperature in regard to power output, heat recovery, and overall cycle efficiency. The method presented can be readily programmed in a computer, for any given gaseous or liquid fuel, to yield accurate evaluations. An X–Y plotter can be utilized to present the results.

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Rice, I. G. "Split Stream Boilers for High-Temperature/High-Pressure Topping Steam Turbine Combined Cycles." Journal of Engineering for Gas Turbines and Power 119, no. 2 (April 1, 1997): 385–94. http://dx.doi.org/10.1115/1.2815586.

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Research and development work on high-temperature and high-pressure (up to 1500°F TIT and 4500 psia) topping steam turbines and associated steam generators for steam power plants as well as combined cycle plants is being carried forward by DOE, EPRI, and independent companies. Aeroderivative gas turbines and heavy-duty gas turbines both will require exhaust gas supplementary firing to achieve high throttle temperatures. This paper presents an analysis and examples of a split stream boiler arrangement for high-temperature and high-pressure topping steam turbine combined cycles. A portion of the gas turbine exhaust flow is run in parallel with a conventional heat recovery steam generator (HRSG). This side stream is supplementary fired opposed to the current practice of full exhaust flow firing. Chemical fuel gas recuperation can be incorporated in the side stream as an option. A significant combined cycle efficiency gain of 2 to 4 percentage points can be realized using this split stream approach. Calculations and graphs show how the DOE goal of 60 percent combined cycle efficiency burning natural gas fuel can be exceeded. The boiler concept is equally applicable to the integrated coal gas fuel combined cycle (IGCC).

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Staub, F. W., S. G. Kimura, C. L. Spiro, and M. W. Horner. "Coal–Water Slurry Combustion in Gas Turbines." Journal of Engineering for Gas Turbines and Power 111, no. 1 (January 1, 1989): 1–7. http://dx.doi.org/10.1115/1.3240222.

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This paper presents preliminary results of a program to investigate the key technologies for burning coal-water slurries in gas turbines. Results are given for slurry atomization and combustion testing and analyses performed at conditions typical for gas turbine applications. Significant progress has been made toward the understanding of slurry combustion and ash deposition phenomena. Confidence has been gained to the extent where elimination of a supplementary pilot fuel can now be projected.

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De Lucia, M., and G. Masotti. "A Scanning Radiation Thermometry Technique for Determining Temperature Distribution in Gas Turbines." Journal of Engineering for Gas Turbines and Power 117, no. 2 (April 1, 1995): 341–46. http://dx.doi.org/10.1115/1.2814100.

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A scanning radiation thermometry technique for determining temperature distributions in gas turbines is presented. The system, an enhancement of an earlier work, can be used by operators even without special training, since the temperature distribution is measured and corrected in terms of the error due to the reflected radiation only on the basis of the turbine’s known geometry and the physical properties of the materials. In the proposed model, the surface-exitent radiances are directly acquired via 360-deg scans. Experimental testing was performed on a static turbine-blading model. Since the angle factors emerged as a notable influence on the accuracy of the model, two angle factor calculation methods, selected for suitability from a literature survey, are exhaustively investigated, and their selection criteria defined.

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Meier, J. G., W. S. Y. Hung, and V. M. Sood. "Development and Application of Industrial Gas Turbines for Medium-Btu Gaseous Fuels." Journal of Engineering for Gas Turbines and Power 108, no. 1 (January 1, 1986): 182–90. http://dx.doi.org/10.1115/1.3239869.

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This paper describes the successful development and application of industrial gas turbines using medium-Btu gaseous fuels, including those derived from biodegradation of organic matters found in sanitary landfills and liquid sewage. The effects on the gas turbine and its combustion system of burning these alternate fuels compared to burning high-Btu fuels, along with the gas turbine development required to use alternate fuels from the point of view of combustion process, control system, gas turbine durability, maintainability and safety, are discussed.

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Bakken, L. E., and L. Skogly. "Parametric Modeling of Exhaust Gas Emission From Natural Gas Fired Gas Turbines." Journal of Engineering for Gas Turbines and Power 118, no. 3 (July 1, 1996): 553–60. http://dx.doi.org/10.1115/1.2816683.

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Increased focus on air pollution from gas turbines in the Norwegian sector of the North Sea has resulted in taxes on CO2. Statements made by the Norwegian authorities imply regulations and/or taxes on NOx emissions in the near future. The existing CO2 tax of NOK 0.82/Sm3 (US Dollars 0.12/Sm3) and possible future tax on NOx are analyzed mainly with respect to operating and maintenance costs for the gas turbine. Depending on actual tax levels, the machine should be operated on full load/optimum thermal efficiency or part load to reduce specific exhaust emissions. Based on field measurements, exhaust emissions (CO2, CO, NOx, N20, UHC, etc.) are established with respect to load and gas turbine performance, including performance degradation. Different NOx emission correlations are analyzed based on test results, and a proposed prediction model presented. The impact of machinery performance degradation on emission levels is particularly analyzed. Good agreement is achieved between measured and predicted NOx emissions from the proposed correlation. To achieve continuous exhaust emission control, the proposed NOx model is implemented to the on-line condition monitoring system on the Sleipner A platform, rather than introducing sensitive emission sensors in the exhaust gas stack. The on-line condition monitoring system forms an important tool in detecting machinery condition/degradation and air pollution, and achieving optimum energy conservation.

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Martinez-Frias, Joel, Salvador M. Aceves, J. Ray Smith, and Harry Brandt. "Thermodynamic Analysis of Zero-Atmospheric Emissions Power Plant." Journal of Engineering for Gas Turbines and Power 126, no. 1 (January 1, 2004): 2–8. http://dx.doi.org/10.1115/1.1635399.

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This paper presents a theoretical thermodynamic analysis of a zero-atmospheric emissions power plant. In this power plant, methane is combusted with oxygen in a gas generator to produce the working fluid for the turbines. The combustion produces a gas mixture composed of steam and carbon dioxide. These gases drive multiple turbines to produce electricity. The turbine discharge gases pass to a condenser where water is captured. A stream of pure carbon dioxide then results that can be used for enhanced oil recovery or for sequestration. The analysis considers a complete power plant layout, including an air separation unit, compressors and intercoolers for oxygen and methane compression, a gas generator, three steam turbines, a reheater, two preheaters, a condenser, and a pumping system to pump the carbon dioxide to the pressure required for sequestration. This analysis is based on a 400 MW electric power generating plant that uses turbines that are currently under development by a U.S. turbine manufacturer. The high-pressure turbine operates at a temperature of 1089 K (1500°F) with uncooled blades, the intermediate-pressure turbine operates at 1478 K (2200°F) with cooled blades and the low-pressure turbine operates at 998 K (1336°F). The power plant has a net thermal efficiency of 46.5%. This efficiency is based on the lower heating value of methane, and includes the energy necessary for air separation and for carbon dioxide separation and sequestration.

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31

Simonich, J. C. "Actuator technologies for active noise control in gas turbines." Journal of Aircraft 33, no. 6 (November 1996): 1174–80. http://dx.doi.org/10.2514/3.47072.

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32

Sulzer, Sabin, Magnus Hasselqvist, Hideyuki Murakami, Paul Bagot, Michael Moody, and Roger Reed. "The Effects of Chemistry Variations in New Nickel-Based Superalloys for Industrial Gas Turbine Applications." Metallurgical and Materials Transactions A 51, no. 9 (June 22, 2020): 4902–21. http://dx.doi.org/10.1007/s11661-020-05845-7.

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Abstract Industrial gas turbines (IGT) require novel single-crystal superalloys with demonstrably superior corrosion resistance to those used for aerospace applications and thus higher Cr contents. Multi-scale modeling approaches are aiding in the design of new alloy grades; however, the CALPHAD databases on which these rely remain unproven in this composition regime. A set of trial nickel-based superalloys for IGT blades is investigated, with carefully designed chemistries which isolate the influence of individual additions. Results from an extensive experimental characterization campaign are compared with CALPHAD predictions. Insights gained from this study are used to derive guidelines for optimized gas turbine alloy design and to gauge the reliability of the CALPHAD databases.

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33

Johnson, M. S. "Prediction of Gas Turbine On- and Off-Design Performance When Firing Coal-Derived Syngas." Journal of Engineering for Gas Turbines and Power 114, no. 2 (April 1, 1992): 380–85. http://dx.doi.org/10.1115/1.2906602.

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This paper describes a procedure used to model the performance of gas turbines designed to fire natural gas (or distillate oil) when fired on medium-Btu fuel, such as coal-derived syngas. Results from such performance studies can be used in the design or analysis of Gasification Combined Cycle (GCC) power plants. The primary difficulty when firing syngas in a gas turbine designed for natural gas is the tendency to drive the compressor toward surge. If the gas turbine has sufficient surge margin and mechanical durability, Gas Turbine Evaluation code (GATE) simulations indicate that net output power can be increased on the order of 15 percent when firing syngas due to the advantageous increase in the ratio of the expander-to-compressor mass flow rates. Three classes of single-spool utility gas turbines are investigated spanning firing temperatures from 1985°F-2500°F (1358 K-1644 K). Performance simulations at a variety of part-load and ambient temperature conditions are described; the resulting performance curves are useful in GCC power plant studies.

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Wenglarz, R. A. "An Approach for Evaluation of Gas Turbine Deposition." Journal of Engineering for Gas Turbines and Power 114, no. 2 (April 1, 1992): 230–34. http://dx.doi.org/10.1115/1.2906577.

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An approach for estimating deposition in gas turbines is described. This approach extrapolates deposition data from lower cost experiments than turbine engine or cascade tests. The purpose is a method to screen candidate fuels and turbine protection methods so that only the most promising need be evaluated in turbine tests. The deposition approach is applied to estimate deposition maintenance intervals for a tested fuel, evaluate benefits of hot gas cleanup, and provide fuel screening criteria.

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35

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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36

Wang, Guoliang, Ning Ge, and Dongdong Zhong. "Numerical Investigation of the Wake Vortex-Related Flow Mechanisms in Transonic Turbines." International Journal of Aerospace Engineering 2020 (August 1, 2020): 1–18. http://dx.doi.org/10.1155/2020/8825542.

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As the core equipment of the power generation system, a gas turbine is an indispensable energy-converting device in the national industry. The flow inside a high-pressure turbine (HPT) is highly unsteady, which has a great influence on the aerothermal performance and structural strength. To better clarify the flow mechanism and guide the advanced design, the basic flow characteristics of transonic turbines are investigated in the paper by a modified scale-adaptive simulation (SAS) model based on the shear stress transport (SST) turbulence model. The numerical results reveal the formation and development of the secondary flow structures such as wake vortex, pressure wave, shock wave, and the interactions among them. The length and frequency characteristics of wake are in good agreement with the large eddy simulation (LES) and the experimental data. Based on the detailed flow information, the local loss analysis is performed using the entropy generation rate. In summary, the wake vortex-related flow is the main origin of unsteadiness and entropy loss in high-pressure turbine cascade.

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37

Yang, Dongfang, Vladimir Pankov, Linruo Zhao, and Prakash Patnaik. "Laser deposited high temperature thin film sensors for gas turbines." Aircraft Engineering and Aerospace Technology 92, no. 1 (January 6, 2020): 2–7. http://dx.doi.org/10.1108/aeat-11-2018-0292.

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Purpose Accurate measurements of the temperature distributions in hot section components are indispensable for the prognostic and health management of gas turbines. Thin film thermocouple (TFTC) sensors, directly fabricated on the surface of a component, add negligible mass and create little or no disturbance to airflow, and therefore, can provide accurate measurements of fast temperature fluctuations of gas turbines. The purpose of this paper is to evaluate TFTC sensors fabricated by combining pulsed laser deposition (PLD) and micromachining techniques (LM). Design/methodology/approach The “dry” PLD/LM fabrication approach allows for excellent control of the chemical composition and physical characteristics of the constituent layers and their interfaces, thus achieving good adhesion of the layers to the substrate. Findings The results of thermal cyclic durability testing of the fabricated TFTC sensors demonstrated that the proposed PLD-based approach can be used to fabricate sensors that are fully functional at temperatures up to 750°C. Analyses of the sensor performance during durability testing revealed: the existence of a threshold temperature below which accurate temperature measurements were achieved; an abrupt drop in the sensor output occurring when the sensor temperature exceeded the threshold value, with a fast recovery of the sensor output once the temperature was reduced below the threshold level; and sensor “training” capable of increasing the threshold value of the TFTC through its exposure to above-the-threshold temperatures. Originality/value The work is the first time to demonstrate that simple PLD and LM processes can be used to fabricate TFTC that are fully functional at temperatures up to 750°C.

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38

Uppal, Tarun, Soumyendu Raha, and Suresh Srivastava. "Inverse Simulation for Gas Turbine Engine Control through Differential Algebraic Inequality Formulation." International Journal of Turbo & Jet-Engines 35, no. 4 (December 19, 2018): 373–83. http://dx.doi.org/10.1515/tjj-2016-0057.

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Abstract Modern day gas turbines are prime movers in land, air and sea. They have stringent performance requirements to meet the complex mission objectives. Optimal control strategies can help them meet their performance objectives more efficiently. A novel inverse simulation method for optimal control and system analysis studies using Differential Algebraic Equality/Inequality (DAE/DAI) technique is brought out in this paper with a case study. The gas turbine model together with safety constraints and performance specifications is represented as a high index DAI/DAE system. The solution for this DAE/DAI system is obtained using a new numerical approach that is capable of handling both equality and inequality constraints on system dynamics. The algorithm involves direct numerical integration of a DAI formulation in a time stepping manner using Sequential Quadratic Programming (SQP) solver that detects and satisfy active constraints at each time step (mesh point). In this unique approach the model and the constraints are always solved together. The method ensures stable solution at each time step, local minimum at each iteration of simulation and provides a regularised basis to the solver. Compared to other existing computationally intensive techniques in usage, this approach is easy, ensures continuous constraint satisfaction and provides a viable option for Model Predictive Control (MPC) of gas turbine engines.

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Rocca, E., P. Steinmetz, and M. Moliere. "Revisiting the Inhibition of Vanadium-Induced Hot Corrosion in Gas Turbines." Journal of Engineering for Gas Turbines and Power 125, no. 3 (July 1, 2003): 664–69. http://dx.doi.org/10.1115/1.1456095.

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Since the 1970s, nothing substantially new has been published in the gas turbine community about the hot corrosion by vanadium and its inhibition, after the “inhibition orthodoxy” based on the formation of magnesium vanadate, was established. However, the experience acquired since the late 1980s with heavy-duty gas turbines burning ash-forming fuels in southern China, shows that the combustion of very contaminated fuels does not entail corrosion nor abundant ash-deposit on gas turbines buckets. Analyses of deposits collected from gas turbines fired with these crude oils showed that the ash-deposit contains a large amount of nickel. These new facts led to revisit the role played by nickel and envisage its possible inhibiting action against the vanadium-induced hot corrosion. A thorough review of the literature on the vanadium-induced corrosion have been carried out, and the study of the nickel effects with respect to magnesium effects on the ash deposit have been performed. Results show that nickel presents an interesting way to substitute magnesium for the inhibition of vanadium-induced hot corrosion. The advantages of nickel with respect to magnesium are to be efficient at alow Ni/V ratio, to produce less abundant, less adherent ash and to act, to some extent, as a self-cleaning agent for the blades of the turbine.

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40

Grondahl, C. M., and M. E. Guiler. "MS3002 Advanced Tech Upgrade Application and Operating Experience." Journal of Engineering for Gas Turbines and Power 113, no. 4 (October 1, 1991): 495–500. http://dx.doi.org/10.1115/1.2906267.

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Modernization of MS3002 gas turbines produced by GE from 1951 to 1973 has been accomplished with the application of advanced technology components in a redesigned turbine hot section. Texas Eastern installed the first modernization package in 1986 and now has 10 units in service totalling more than 135,000 operating hours. This paper presents the user’s motivation to refurbish 30-year-old gas turbines, including details of the uprate installation and subsequent operating experience. Specifics of the advanced technology components in these units are provided including their impact on unit performance and reliability.

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41

Valenti, Michael. "Turbines for Peace." Mechanical Engineering 122, no. 08 (August 1, 2000): 70–72. http://dx.doi.org/10.1115/1.2000-aug-5.

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This article discusses that military-sponsored research tools can improve the machines that drive civil applications. The Defense Evaluation and Research Agency (DERA) researchers tested the engine of the legendary DeHavilland Vampire single seat jet fighter in the late 1940s. This Vampire is owned by Fred Ihlenburg, president of Yakity Yaks Inc., an importer of foreign military aircraft, based in Aurora, Oregon. DERA is investigating heat transfer on turbine blades to help gas turbine manufacturers develop a cooling system that will keep blades at an optimum temperature while minimizing losses in engine performance. More efficient cooling means less air is bled from the compressor, thus improving performance while extending blade life. This work was co-funded by the Central European Commission under the Brite Euram Fourth-Framework Initiative, which is part of the European Union’s strategy to enhance European global competitiveness, and Britain’s Department of Trade and Industry’s Civil Aircraft Research and Technology Demonstration Program. The British program aims to advance the capabilities of the United Kingdom’s civil aerospace companies.

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42

Beck, D. S. "Optimization of Regenerated Gas Turbines." Journal of Engineering for Gas Turbines and Power 118, no. 3 (July 1, 1996): 654–60. http://dx.doi.org/10.1115/1.2816698.

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An algorithm for the optimization of regenerated gas turbines is given. For sets of inputs that are typical for automotive applications, the optimum cycle pressure ratio and a set of optimized regenerator parameters that maximize thermal efficiency are given. A second algorithm, an algorithm for sizing regenerators based on outputs of the optimization algorithm, is given. With this sizing algorithm, unique regenerator designs can be determined for many applications based on the presented optimization data. Results of example sizings are given. The data indicate that one core (instead of two cores) should be used to maximize thermal efficiency. The data also indicate that thermal efficiencies of over 50 percent should be achievable for automotive applications if ceramic turbines are used.

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43

Alozie, O., Y. G. Li, M. Diakostefanis, X. Wu, X. Shong, and W. Ren. "Assessment of degradation equivalent operating time for aircraft gas turbine engines." Aeronautical Journal 124, no. 1274 (January 9, 2020): 549–80. http://dx.doi.org/10.1017/aer.2019.153.

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ABSTRACTThis paper presents a novel method for quantifying the effect of ambient, environmental and operating conditions on the progression of degradation in aircraft gas turbines based on the measured engine and environmental parameters. The proposed equivalent operating time (EOT) model considers the degradation modes of fouling, erosion, and blade-tip wear due to creep strain, and expresses the actual degradation rate over the engine clock time relative to a pre-defined reference condition. In this work, the effects of changing environmental and engine operating conditions on the EOT for the core engine booster compressor and the high-pressure turbine were assessed by performance simulation with an engine model. The application to a single and multiple flight scenarios showed that, compared to the actual engine clock time, the EOT provides a clear description of component degradation, prediction of remaining useful life, and sufficient margin for maintenance action to be planned and performed before functional failure.

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44

Brun, Klaus, Rainer Kurz, and Harold R. Simmons. "Aerodynamic Instability and Life-Limiting Effects of Inlet and Interstage Water Injection Into Gas Turbines." Journal of Engineering for Gas Turbines and Power 128, no. 3 (March 1, 2004): 617–25. http://dx.doi.org/10.1115/1.2135819.

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Gas turbine power enhancement technologies, such as inlet fogging, interstage water injection, saturation cooling, inlet chillers, and combustor injection, are being employed by end users without evaluating the potentially negative effects these devices may have on the operational integrity of the gas turbine. Particularly, the effect of these add-on devices, off-design operating conditions, nonstandard fuels, and compressor degradation∕fouling on the gas turbine’s axial compressor surge margin and aerodynamic stability is often overlooked. Nonetheless, compressor aerodynamic instabilities caused by these factors can be directly linked to blade high-cycle fatigue and subsequent catastrophic gas turbine failure; i.e., a careful analysis should always proceed the application of power enhancement devices, especially if the gas turbine is operated at extreme conditions, uses older internal parts that are degraded and weakened, or uses nonstandard fuels. This paper discusses a simplified method to evaluate the principal factors that affect the aerodynamic stability of a single-shaft gas turbine’s axial compressor. As an example, the method is applied to a frame-type gas turbine and results are presented. These results show that inlet cooling alone will not cause gas turbine aerodynamic instabilities, but that it can be a contributing factor if for other reasons the machine’s surge margin is already slim. The approach described herein can be employed to identify high-risk applications and bound the gas turbine operating regions to limit the risk of blade life reducing aerodynamic instability and potential catastrophic failure.

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Jansen, M., T. Schulenberg, and D. Waldinger. "Shop Test Result of the V64.3 Gas Turbine." Journal of Engineering for Gas Turbines and Power 114, no. 4 (October 1, 1992): 676–81. http://dx.doi.org/10.1115/1.2906641.

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The V64.3 60-MW combustion turbine is the first of a new generation of high-temperature gas turbines, designed for 50 and 60 Hz simple cycle, combined cycle, and cogeneration applications. The prototype engine was tested in 1990 in the Berlin factories under the full range of operation conditions. It was equipped with various measurement systems to monitor pressures, gas and metal temperatures, clearances, strains, vibrations, and exhaust emissions. The paper describes the engine design, the test facility and instrumentation, and the engine performance. Results are given for turbine blade temperatures, compressor and turbine vibrations, exhaust gas temperature, and NOx emissions for combustion of natural gas and fuel oil.

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Cunha, F. J., and M. K. Chyu. "Trailing-Edge Cooling for Gas Turbines." Journal of Propulsion and Power 22, no. 2 (March 2006): 286–300. http://dx.doi.org/10.2514/1.20898.

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47

Reed, John A., and Abdollah A. Afjeh. "Computational Simulation of Gas Turbines: Part 1—Foundations of Component-Based Models." Journal of Engineering for Gas Turbines and Power 122, no. 3 (May 15, 2000): 366–76. http://dx.doi.org/10.1115/1.1287490.

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Designing and developing new aerospace propulsion systems is time-consuming and expensive. Computational simulation is a promising means for alleviating this cost, but requires a flexible software simulation system capable of integrating advanced multidisciplinary and multifidelity analysis methods, dynamically constructing arbitrary simulation models, and distributing computationally complex tasks. To address these issues, we have developed Onyx, a Java-based object-oriented domain framework for aerospace propulsion system simulation. This paper presents the design of a common engineering model formalism for use in Onyx. This approach, which is based on hierarchical decomposition and standardized interfaces, provides a flexible component-based representation for gas turbine systems, subsystems and components. It allows new models to be composed programmatically or visually to form more complex models. Onyx’s common engineering model also supports integration of a hierarchy of models which represent the system at differing levels of abstraction. Selection of a particular model is based on a number of criteria, including the level of detail needed, the objective of the simulation, the available knowledge, and given resources. The common engineering model approach is demonstrated by developing gas turbine component models which will be used to compose a gas turbine engine model in Part 2 of this paper. [S0742-4795(00)02303-6]

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48

Ito, K., R. Yokoyama, and Y. Matsumoto. "Optimal Operation of Cogeneration Plants With Steam-Injected Gas Turbines." Journal of Engineering for Gas Turbines and Power 117, no. 1 (January 1, 1995): 60–66. http://dx.doi.org/10.1115/1.2812782.

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The effect of introducing steam-injected gas turbines into cogeneration plants is investigated from economical and energy-saving aspects on the basis of a mathematical programming approach. An optimal planning method is first presented by which the operational strategy is assessed so as to minimize the hourly running cost. Then, a case study is carried out on a plant used for district heating and cooling. Through the study, it is ascertained that the proposed method is a useful tool for the operational planning of steam-injected gas turbine plants, and that these plants can be attractive from economical and energy-saving viewpoints as compared with both simple-cycle gas turbine plus waste heat boiler plants and conventional energy supply ones.

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Schlottke, Adrian, and Bernhard Weigand. "Two-Phase Flow Phenomena in Gas Turbine Compressors with a Focus on Experimental Investigation of Trailing Edge Disintegration." Aerospace 8, no. 4 (March 26, 2021): 91. http://dx.doi.org/10.3390/aerospace8040091.

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Two-phase flow in gas turbine compressors occurs, for example, at heavy rain flight condition or at high-fogging in stationary gas turbines. The liquid dynamic processes are independent of the application. An overview on the processes and their approach in literature is given. The focus of this study lies on the experimental investigation of the trailing edge disintegration. In the experiments, shadowgraphy is used to observe the disintegration of a single liquid rivulet with constant liquid mass flow rate at the edge of a thin plate at different air flow velocities. A two side view enables calculating droplet characteristics with high accuracy. The results show the asymptotic behavior of the ejected mean droplet diameters and the disintegration period. Furthermore, it gives a detailed insight into the droplet diameter distribution and the spreading of the droplets perpendicular to the air flow.

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Smith, A. R., J. Klosek, and D. W. Woodward. "Next-Generation Integration Concepts for Air Separation Units and Gas Turbines." Journal of Engineering for Gas Turbines and Power 119, no. 2 (April 1, 1997): 298–304. http://dx.doi.org/10.1115/1.2815575.

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The commercialization of Integrated Gasification Combined Cycle (IGCC) Power has been aided by concepts involving the integration of a cryogenic air separation unit (ASU) with the gas turbine combined-cycle module. Other processes, such as coal-based ironmaking and combined power/industrial gas production facilities, can also benefit from the integration. It is known and now widely accepted that an ASU designed for “elevated pressure” service and optimally integrated with the gas turbine can increase overall IGCC power output, increase overall efficiency, and decrease the net cost of power generation when compared to nonintegrated facilities employing low-pressure ASUs. The specific gas turbine, gasification technology, NOx emission specification, and other site specific factors determine the optimal degree of compressed air and nitrogen stream integration. Continuing advancements in both air separation and gas turbine technologies offer new integration opportunities to improve performance and reduce costs. This paper reviews basic integration principles and describes next-generation concepts based on advanced high pressure ratio gas turbines, Humid Air Turbine (HAT) cycles and integration of compression heat and refrigeration sources from the ASU. Operability issues associated with integration are reviewed and control measures are described for the safe, efficient, and reliable operation of these facilities.

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Journal articles on the topic 'Aerospace gas turbines'

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