Journal articles on the topic 'Aircraft gas-turbines'
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1
Wells, Robert L. "AIRCRAFT GAS TURBINES." Journal of the American Society for Naval Engineers 61, no. 4 (March 18, 2009): 785–98. http://dx.doi.org/10.1111/j.1559-3584.1949.tb02655.x.
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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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Shende, R. W., and S. K. Sane. "Squeeze Film Damping for Aircraft Gas Turbines." Defence Science Journal 38, no. 4 (January 13, 1988): 439–56. http://dx.doi.org/10.14429/dsj.38.5874.
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Valenti, Michael. "A Drier Way To Clean Turbines." Mechanical Engineering 120, no. 03 (March 1, 1998): 98–100. http://dx.doi.org/10.1115/1.1998-mar-7.
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A high-pressure injection system that needs less water to clean gas turbines than conventional methods can reduce equipment maintenance costs for aircraft, offshore platforms, and power plants. Gas Turbine Efficiency (GTE) in Jarfalla, Sweden, has developed a high-pressure injection system that cleans turbines using atomized droplets and needs 90 percent less liquid than previous methods. With this technique, the operators of offshore oil platforms, power plants, refineries, and aircraft in several countries are reducing the purchase costs of new fluids, the disposal costs of spent cleaning fluids, and maintenance downtime. In creating their washing system, designers considered the differences in cleaning aviation and stationary engines. The turbine-washing system is available in mobile versions for aircraft engines and permanently installed versions, for the off-line cleaning of stationary turbines. GTE also designed two models to serve the very small and very large turbines. The GTE 30 A services the small turbines, ranging from 0.5 to 10 megawatts, that are used in industrial, power-generation, marine, and test-cell applications as well as turboprop aircraft, turbofan craft, and helicopters.
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Gregory, Brent A. "How Many Turbine Stages?" Mechanical Engineering 139, no. 05 (May 1, 2017): 56–57. http://dx.doi.org/10.1115/1.2017-may-5.
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This article discusses various stages of turbines and the importance of having more stages in turbine design. The article also highlights reasons that determine the designer’s choice to select the number of turbine stages for a given design of gas turbine. The highest performance turbines are defined by lower work requirements and slower velocities in the gas path. The fundamental factors determining performance might be relegated to only two factors: demand on the turbine and axial velocity. Aircraft engine technologies drive new initiatives because of the need to increase firing temperature and dramatically improve efficiency for substantially less weight. Also, the expansion across each stage determined the annulus area so that the optimums implied by the Pearson chart were largely ignored in the article. Developments in aircraft engine gas turbines have forced heavy frame gas turbines’ original equipment manufacturers to rethink many historical paradigms.
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Mannan, S. K., and Shalesh J. Patel. "INCONEL Alloy 783: An Oxidation Resistant, Low Expansion Superalloy for Gas and Steam Turbine Applications." Materials Science Forum 546-549 (May 2007): 1271–76. http://dx.doi.org/10.4028/www.scientific.net/msf.546-549.1271.
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Recently developed alloy 783 (nominal composition of Ni-34Co-26Fe-5.4Al-3Nb-3Cr, UNS R30783) is precipitation strengthened by Ni3Al-type gamma prime and NiAl-type beta phases. The alloy is being used for seals/casings in aircraft gas turbines and for bolting in steam turbines due to its low co-efficient of thermal expansion, high strength, and good oxidation resistance. It has also been specified for other aircraft gas turbine components such as rings for casings and shrouds. This paper presents the alloy’s basic characteristics, applications, and hot and cold workability.
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Langston, Lee S. "Riding the Surge." Mechanical Engineering 135, no. 05 (May 1, 2013): 37–41. http://dx.doi.org/10.1115/1.2013-may-2.
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This article explores the advantages of gas turbines in the marine industry. Marine gas turbines, which are designed specifically for use on ships, have long been one of the segments of the gas turbine market. One advantage that gas turbines have over conventional marine diesels is volume. Gas turbines are the prime movers for the modern combined cycle electric power plant. Both CFM International (a joint venture of General Electric and France’s Snecma) and Pratt & Whitney are working on new engines for this multibillion dollar single-aisle, narrow-body market. Pratt & Whitney’s new certified PW1500G geared turbofans will have a first flight powering the first Bombardier CSeries aircraft. On land, sea, and air, the surge in gas turbine production is remarkable. The experts suggest that what the steam engine was to the 19th century and the internal combustion engine was to the 20th, the gas turbine might be to the 21st century: the ubiquitous prime mover of choice.
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Langston, Lee S. "Old and New." Mechanical Engineering 141, no. 06 (June 1, 2019): 38–43. http://dx.doi.org/10.1115/1.2019-jun2.
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As prime movers go, gas turbines are virtually brand new, compared to, say, wind and water turbines which have been around for millennia. But they have also reached a considerable level of maturity. Gas turbines now dominate both the world’s aircraft propulsion and a good portion of electric power generation. The fortunes of the industry are not uniform, however. The commercial jet engine market is robust and growing; the military jet engine, electric power, and other markets have been relatively flat or declining. But those are the sectors where the possibilities lie. They aren’t new, but they have the potential for renewal. This study delves deeper into the current status and trends in theworldwide gas turbine market.
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Cowles, B. A. "High cycle fatigue in aircraft gas turbines—an industry perspective." International Journal of Fracture 80, no. 2-3 (April 1996): 147–63. http://dx.doi.org/10.1007/bf00012667.
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Rohacs, Jozsef, Istvan Jankovics, Istvan Gal, Jerzy Bakunowicz, Giuseppe Mingione, and Antonio Carozza. "Small Aircraft Infrared Radiation Measurements Supporting the Engine Airframe Aero-thermal Integration." Periodica Polytechnica Transportation Engineering 47, no. 1 (March 12, 2018): 51–63. http://dx.doi.org/10.3311/pptr.11514.
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The large, EU Supported ESPOSA (Efficient Systems and propulsion for Small Aircraft) project has developed new small gas turbines for small aircraft. One of the important tasks was the engine - airframe aero-thermal radiation integration that included task of minimizing the infrared radiation of the small aircraft, too. This paper discusses the factors influencing on the aircraft infrared radiation, its possible simulation and measurements and introduces the results of small aircraft infrared radiation measurements. The temperature of aircraft hot parts heated by engines were determined for validation of methodology developed and applied to engine - aircraft thermal integration.
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Langston, Lee S. "Changing the Game." Mechanical Engineering 130, no. 05 (May 1, 2008): 25–29. http://dx.doi.org/10.1115/1.2008-may-2.
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This article reviews potentially radical advances in gas turbines that came in all shapes and sizes in 2007. Gas turbine production is now a $30 billion industry, one that has been dominated, except for a stretch in the late 1990s, by commercial and military aviation. In its 70-year history, the gas turbine has become one of society’s most important and versatile energy conversion, which is relatively inert. Fuel converted to power through a gas turbine is as kinetic a substance as you can find, and one that can create great wealth. In the $21.8 billion aviation market, nearly 80 percent is for commercial aircraft engines, while the dominance of electrical generation in the $10.5 billion non-aviation market is even greater. New aircraft represents advances for commercial aviation, but commercial jet engines are themselves the key to future growth of the airline industry. While the aviation market has seen steady growth over the past decade or so, the non-aviation market for gas turbines has a noticeable production spike.
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Lakshminarasimha, A. N., M. P. Boyce, and C. B. Meher-Homji. "Modeling and Analysis of Gas Turbine Performance Deterioration." Journal of Engineering for Gas Turbines and Power 116, no. 1 (January 1, 1994): 46–52. http://dx.doi.org/10.1115/1.2906808.
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The effects of performance deterioration in both land and aircraft gas turbines are presented in this paper. Models for two of the most common causes of deterioration, viz., fouling and erosion, are presented. A stage-stacking procedure, which uses new installed engine field data for compressor map development, is described. The results of the effect of fouling in a powerplant gas turbine and that of erosion in a aircraft gas turbine are presented. Also described are methods of fault threshold quantification and fault matrix simulation. Results of the analyses were found to be consistent with field observations.
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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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Merrington, G., Oh-Kyu Kwon, G. Goodwin, and B. Carlsson. "Fault Detection and Diagnosis in Gas Turbines." Journal of Engineering for Gas Turbines and Power 113, no. 2 (April 1, 1991): 276–82. http://dx.doi.org/10.1115/1.2906559.
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Modern military aircraft are fitted with Engine Monitoring Systems (EMS), which have the potential to provide maintenance personnel with valuable information for diagnosing engine faults and assessing engine condition. In this study, analytical redundancy methods have been applied to gas turbine engine transient data with the view to extracting the desired fault information. The basic idea is to use mathematical models to interrelate the measured variables and then monitor the effects of fault conditions on the new estimates of the model parameters. In most of the existing literature the models used are assumed to be perfect with the primary source of error arising from the measurement noise. In the technique to be described, a new method of quantifying the effects of changes in the operating conditions is presented when simplified models are employed. The technique accounts for undermodeling effects and errors arising from linearization of an inherently nonlinear system. Results obtained show a marked improvement over those obtained with traditional methods.
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Langston, Lee S. "Fahrenheit 3,600." Mechanical Engineering 129, no. 04 (April 1, 2007): 34–37. http://dx.doi.org/10.1115/1.2007-apr-3.
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This article illustrates capabilities of gas turbines to be able to work in extremely elevated temperatures. The turbine airfoils in the new F135 jet engine that powers the Joint Strike Fighter (JSF) Lightning II are capable of operating at these extreme temperatures. The F135 gas turbine is the first production jet engine in this new 3,600°F class, designed to withstand these highest, record-breaking turbine inlet temperatures. The JSF engine is just one product in the $3.7 billion military gas turbine market, which includes jet engine production for the world’s fighter aircraft military cargo, transport, refuelling, and special-purpose aircraft. The article also discusses the features of H Class, which is the largest electric power gas turbine that has been interpreted as an abbreviation for humongous. Non-aviation gas turbines consist of electrical power generation, mechanical drive, and marine. The largest segment of that market by far is electrical power generation, in simple cycle, combined cycle, and cogeneration. Forecast International predicts significant growth in coming years in demand for gas turbine electrical power generation, rising from $8.6 billion in 2006 to a projected $13.5 billion in 2008, a 60 percent increase.
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Han, Je-Chin, and Srinath Ekkad. "Recent Development in Turbine Blade Film Cooling." International Journal of Rotating Machinery 7, no. 1 (2001): 21–40. http://dx.doi.org/10.1155/s1023621x01000033.
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Gas turbines are extensively used for aircraft propulsion, land-based power generation, and industrial applications. Thermal efficiency and power output of gas turbines increase with increasing turbine rotor inlet temperature (RIT). The current RIT level in advanced gas turbines is far above the .melting point of the blade material. Therefore, along with high temperature material development, a sophisticated cooling scheme must be developed for continuous safe operation of gas turbines with high performance. Gas turbine blades are cooled internally and externally. This paper focuses on external blade cooling or so-called film cooling. In film cooling, relatively cool air is injected from the inside of the blade to the outside surface which forms a protective layer between the blade surface and hot gas streams. Performance of film cooling primarily depends on the coolant to mainstream pressure ratio, temperature ratio, and film hole location and geometry under representative engine flow conditions. In the past number of years there has been considerable progress in turbine film cooling research and this paper is limited to review a few selected publications to reflect recent development in turbine blade film cooling.
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Tammineni, S. V., A. R. Rao, J. P. Scanlan, P. A. S. Reed, and A. J. Keane. "A knowledge-based system for cost modelling of aircraft gas turbines." Journal of Engineering Design 20, no. 3 (June 2009): 289–305. http://dx.doi.org/10.1080/09544820701870805.
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Kundu, B., D. Ghosh, and S. Ghosh. "Relative Stress Analysis of Gas Turbine Blade for Various Alloying Materials." Journal of Physics: Conference Series 2070, no. 1 (November 1, 2021): 012176. http://dx.doi.org/10.1088/1742-6596/2070/1/012176.
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Abstract Gas turbines provide a reliable and efficient production of power in both pilot power plants and aircraft propulsion. The operating cost of the modern gas turbines is greatly influenced by the durability of hot section components. To cope up with the increasing temperature, there has been an evolution of new generation blade materials. At elevated temperature conditions, thermal stress and resulting deformations can affect the power developed and efficiency. In this paper a finite element simulation has been made on a fixed blade profile to explore various factors affecting the turbine blade. Variety of existing and new generation materials have been considered a under a boundary condition of constant high pressure and high Operating temperature was varied between 1000°C-1400°C. The development of stress and deformation along with the heat flux have been studied for finding the most effective manufacturing alloy for gas turbines.
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Zaita, A. V., G. Buley, and G. Karlsons. "Performance Deterioration Modeling in Aircraft Gas Turbine Engines." Journal of Engineering for Gas Turbines and Power 120, no. 2 (April 1, 1998): 344–49. http://dx.doi.org/10.1115/1.2818128.
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Steady-state performance models can be used to evaluate a new engine’s baseline performance. As a gas turbine accumulates operating time in the field, its performance deteriorates due to fouling, erosion, and wear. This paper presents the development of a model for predicting the performance deterioration of aircraft gas turbines. The model accounts for rotating component deterioration based on the aircraft mission profiles and environmental conditions and the engine’s physical and design characteristics. The methodology uses data correlations combined with a stage stacking technique for the compressor and a tip rub model, along with data correlations for the turbine to determine the amount of performance deterioration. The performance deterioration model interfaces with the manufacturer’s baseline engine simulation model in order to create a deteriorated performance model for that engine.
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Song, Q., and M. J. Grimble. "Design of a Multivariable Neural Controller and Its Application to Gas Turbines." Journal of Dynamic Systems, Measurement, and Control 119, no. 3 (September 1, 1997): 565–67. http://dx.doi.org/10.1115/1.2801295.
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The algorithm for a multivariable controller using neural network is based on a discrete-time fixed controller and the neural network provides a compensation signal to suppress the nonlinearity. The multivariable neural controller is easy to train and applied to an aircraft gas turbine plant.
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Langston, Lee S. "Clear Skies Ahead." Mechanical Engineering 138, no. 06 (June 1, 2016): 38–43. http://dx.doi.org/10.1115/1.2016-jun-3.
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This article discusses various fields where gas turbines can play a vital role. Building engines for commercial jetliners is the largest market segment for the gas turbine industry; however, it is far from being the only one. One 2015 military gas turbine program of note was the announcement of an U.S. Air Force competition for an innovative design of a small turbine engine, suitable for a medium-size drone aircraft. The electrical power gas turbine market experienced a sharp boom and bust from 2000 to 2002 because of the deregulation of many electric utilities. Since then, however, the electric power gas turbine market has shown a steady increase, right up to present times. Coal-fired plants now supply less than 5 percent of the electrical load, having been largely replaced by new natural gas-fired gas turbine power plants. Working in tandem with renewable energy power facilities, the new fleet of gas turbines is expected to provide reliable, on-demand electrical power at a reasonable cost.
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Langston, Lee S. "Anticipated but Unwelcome." Mechanical Engineering 140, no. 06 (June 1, 2018): 37–41. http://dx.doi.org/10.1115/1.2018-jun-2.
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This article provides the latest trends in the gas turbines market and their future outlook. The last three years of operation have generated more profit for the commercial airline industry than the previous 30 years combined. That money has led to new orders for commercial aircraft and as a result, production of commercial aviation gas turbines is in full swing. Engine manufacturers such as Pratt&Whitney, Rolls-Royce, General Electric, Safran, and others have taken this surge in orders as an incentive to develop new technology. The launch of a new jet engine by a manufacturer can be a multi-billion dollar effort. Financial projections and executive careers hang on a smooth roll-out of the new technology.
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DAHL, G. "Engine control and low-NOx combustion for hydrogen fuelled aircraft gas turbines." International Journal of Hydrogen Energy 23, no. 8 (August 1998): 695–704. http://dx.doi.org/10.1016/s0360-3199(97)00115-8.
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Li, Jiangpeng, Ziti Liu, and Ruoxuan Ye. "Current Status and Prospects of Gas Turbine Technology Application." Journal of Physics: Conference Series 2108, no. 1 (November 1, 2021): 012009. http://dx.doi.org/10.1088/1742-6596/2108/1/012009.
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Abstract The gas turbine is widely used in various fields, including powering aircraft, ships, trains, and electrical generators. This paper reviews multiple researches about two usages of gas turbines, including power generation and propulsion in aerospace. To be specific, two types of gas turbines have been considered in the power generation section. The first one is the micro-scale turbine, and its working principle has been introduced in section 2.1.1. In addition, six diverse kinds of gas turbines, sorted by a different manufacturer, are introduced in 2.1.2, and it has been found out that, compared to its counterpart, EnerTwin is obviously more sustainable. At the same time, both of them generally cost the same. The second type of gas turbine is used in a combined cycle power plant (CCPP), a popular power station. The working principle of CCPP is introduced in 2.2.1, while several optimization methods are illustrated in 2.2.2, including solar thermal power methods and other novel methods. The result indicates that the most popular method of optimizing the combined cycle gas turbine is integrating an additional unit. One of those outstanding technics is the integrated solar-combined cycle, contributing to 64% of fuel saving with 2.8% of output reduction.
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Langston, Lee S. "Breaking the Barriers." Mechanical Engineering 134, no. 05 (May 1, 2012): 32–37. http://dx.doi.org/10.1115/1.2012-may-2.
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This article explores the new developments in the field of gas turbines and the recent progress that has been made in the industry. The gas turbine industry has had its ups and downs over the past 20 years, but the production of engines for commercial aircraft has become the source for most of its growth of late. Pratt & Whitney’s recent introduction of its new geared turbofan engine is an example of the primacy of engine technology in aviation. Many advances in commercial aviation gas turbine technology are first developed under military contracts, since jet fighters push their engines to the limit. Distributed generation and cogeneration, where the exhaust heat is used directly, are other frontiers for gas turbines. Work in fluid mechanics, heat transfer, and solid mechanics has led to continued advances in compressor and turbine component performance and life. In addition, gas turbine combustion is constantly being improved through chemical and fluid mechanics research.
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Wee, Sunguk, Keekeun Kim, Kibum Park, and Changsung Seok. "Study on Creep Damage of Ni-Based Superalloy Caused by Variable Load Conditions at Elevated Temperatures." Materials 14, no. 22 (November 18, 2021): 6971. http://dx.doi.org/10.3390/ma14226971.
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Higher fatigue and creep resistance at high temperatures are the essential properties for materials such as those used in gas turbines for power generation and aircraft turbines. Therefore, the nickel-based superalloy CMSX-4 was developed through single-crystal casting to satisfy these requirements. In this study, the CMSX-4 creep test results reported by previous researchers were used to mathematically derive an equation to estimate the amount of creep damage occurring under variable load conditions. In addition, low-cycle fatigue tests were performed, and the effect of creep damage occurring during fatigue on material failure was described.
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Kerr, L. J., T. S. Nemec, and G. W. Gallops. "Real-Time Estimation of Gas Turbine Engine Damage Using a Control-Based Kalman Filter Algorithm." Journal of Engineering for Gas Turbines and Power 114, no. 2 (April 1, 1992): 187–95. http://dx.doi.org/10.1115/1.2906571.
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A second-generation Kalman filter algorithm is described that has sufficient accuracy and response for real-time detection and estimation of gas turbine engine gas path damage caused by normal wear, mechanical failures, and ingestion of foreign objects. The algorithm was developed for in-flight operation of aircraft engines but also has application for marine and industrial gas turbines. The control measurement and microcomputer requirements are described. The performance and sensitivity to engine transients and measurement errors is evaluated. The algorithm is demonstrated with actual engine data of ice and bird ingestion tests.
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Tovkach, Serhii. "Закони керування авіаційним газотурбінним двигуном з турбовентиляторною приставкою." Aerospace Technic and Technology, no. 4sup1 (August 24, 2023): 70–74. http://dx.doi.org/10.32620/aktt.2023.4sup1.10.
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The main aspects of the general task of integrating an aviation engine (AE) with a turbofan additional unit (TAU) of a multi-mode aircraft are the selection of the scheme and design parameters of the AE with the TAU (including parameters of the work process), as well as methods and means of automatic control of the AE with the TAU for better matching its characteristics with certain flight modes. These two tasks are closely interrelated: on the one hand, when determining the appearance of the aircraft and its power plant (PP), it is necessary to consider what means will ensure the adaptation of its characteristics to the variable flight mode, and on the other hand, the purpose of the aircraft, its parameters and parameters of the PP, and the flight modes mostly determine the choice of control laws. The subject of the research is the formation of the laws of control of the aviation gas turbine engine with TAU. The goal is to improve the dynamic characteristics of the aviation gas turbine engine by applying adaptive control of the gas turbine engine with the use of wireless information exchange technologies. Objectives: to generalize the concept of adaptive control at the stage of determining the appearance of an engine with TAU; to determine the methods of regulating the GTE with TAU and their influence on the speed characteristics; to describe the process of formation of the laws governing AE with TAU; to investigate thermal processes in order to find functional dependencies in the optimal control of gas turbines with TAU. Research methods: system analysis, mathematical and computer modeling were used in the formation of control laws; the methods of philosophical knowledge were used to build an approach to the design of adaptive control systems of gas turbines with TAU. The theory of aircraft engines, the theory of differential equations, difference grids, and numerical methods were used to optimize the control of gas turbines with TAU. Results: methods of regulating the GTE with TAU and their influence on the speed characteristics of the aviation engine; formulas for researching the thermal processes of the working blades of the GTE with TAU in order to form the influence of the regulator on the executive mechanisms. Scientific and practical novelty: formation of a paradigm for the development of models of adaptive control of GTE with TAU, considering different flight modes of the aircraft and engine operation modes. The selection of control laws using multi-parameter optimization methods for finding the relationship between structural and component schemes of the gas generator and turbofan additional unit. The character of the engine thrust change depending on the input temperature is shown, which in turn, will allow to increase the efficiency of the fan and obtain a thrust reserve. The research directions of the temperature field and stress field were formed.
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Longston, Lee. "Electrically Charged." Mechanical Engineering 124, no. 06 (June 1, 2002): 50–52. http://dx.doi.org/10.1115/1.2002-jun-3.
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This article focuses on gas turbines that were produced in 2001 spanning a wide range of capacities. As the engineer's most versatile energy converters, gas turbines producing thrust power continued in 2001 to propel most of the world's aircraft, both military and commercial. The largest commercial jet engines today can produce as much as 120,000 pounds thrust, or some 534,000 Newton. More natural gas pipeline capacity will be added to feed the surge in gas-driven electric power plants that have been corning online in the United States and other parts of the world. The gas turbine may come to be used in a new, commercially promising closed-cycle configuration. A South African company has been working on plans to build and test a prototype of a closed-cycle electric power gas turbine, which uses helium gas as the working fluid and a helium-cooled nuclear reactor to provide heat to power the cycle. If the gas turbine-nuclear reactor power plant is successful, the gas turbine may be the key to yet another energy conversion device, as it has been with record-setting numbers of combined-cycle plants installed worldwide.
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Moukalled, F., and I. Lakkis. "Computer-Aided Analysis of Gas Turbine Cycles." International Journal of Mechanical Engineering Education 22, no. 3 (July 1994): 209–27. http://dx.doi.org/10.1177/030641909402200306.
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This paper describes a microcomputer-based, interactive, and menu-driven software package designed to help mechanical engineering students to understand gas turbines and to allow them to conduct more analysis of gas turbine cycles than they would normally be able to do by hand-calculation. The program deals with gas turbine cycle analysis so the acronym GTCA is used. GTCA is written in the Pascal computer language and runs on IBM PC, or compatible, computers. Improvements to the basic Brayton cycle, including three compressor and turbine stages, reheater, heat exchanger, intercooler, and precooler are incorporated into the program. The package is highly flexible and allows the user to model cycle schemes formed of any combination of these elements and to handle both shaft power turbines and aircraft turbojet and turbofan turbines. An important feature of the program is its ability to solve for any unknown variables. In addition to this, the program provides a schematic of the turbine plant layout and a temperature-entropy diagram of the cycle, and permits the plotting of the variation of any quantity versus any other quantity. This option enables the student to easily study and understand the effects of changing design variables on the overall performance of the cycle and permits its optimization. The statistical survey conducted along with the examples presented demonstrate the capabilities of the package as a teaching tool.
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Walsh, P. N., J. M. Quets, and R. C. Tucker. "Coatings for the Protection of Turbine Blades From Erosion." Journal of Engineering for Gas Turbines and Power 117, no. 1 (January 1, 1995): 152–55. http://dx.doi.org/10.1115/1.2812764.
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Many types of turbines, including aircraft gas turbines, steam turbines, and power recovery turbines, suffer from solid particle erosion caused by a variety of materials ingested into the machines. Utilization of various laboratory erosion tests tailored to the specific application by using various erodents, temperatures, velocities, and angles of impact, have been shown to be effective in the development and selection of coatings for the erosion protection of turbine blades and other components. Detonation gun coatings have demonstrated their efficacy in providing substantial protection in many situations. It has now been shown that several tungsten carbide and chromium carbide Super D-Gun™ coatings not only have better erosion resistance than their D-Gun analogs, but cause little or no degradation of the fatigue properties of the blade alloys. Nonetheless, caution should be employed in the application of any laboratory data to a specific situation and additional testing done as warranted by the turbine designer.
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Wilson, Jay M., and Henry Baumgartner. "A New Turbine for Natural Gas Pipelines." Mechanical Engineering 121, no. 05 (May 1, 1999): 72–74. http://dx.doi.org/10.1115/1.1999-may-7.
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The new Cooper-Bessemer power turbine is a high-efficiency, center frame-mounted, three-stage unit that can be driven by either the existing RB211-24 gas generator or the new improved version. The upgraded gas generator combined with the new power turbine offers an increase in nominal output from 28.4 MW (38,000 hp) to 31.8 MW (42,600 hp). The new coupled turbine, now being tested, is called the Coberra 6761. Besides improving core engine performance, the program's objectives included improved fuel efficiency and reliability, and easier site serviceability; extension of the modular concept from the gas generator into the power turbine with improvements in sealing, materials, and temperature capability as well as interchangeability of both upgraded turbines with existing hardware. The Rolls-Royce industrial RB211 turbine, derived from an aircraft engine, is the basis for the gas generator end of Cooper Energy Services' Coberra coupled turbines. The power turbine design capacity has a significant effect on the power at a given speed. The flow capacity was optimized to achieve the best thermal efficiency and lower IP speeds to optimize IP compressor efficiency and permit future throttle push.
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Tsujikawa, Y., and M. Nagaoka. "Determination of Cycle Configuration of Gas Turbines and Aircraft Engines by an Optimization Procedure." Journal of Engineering for Gas Turbines and Power 113, no. 1 (January 1, 1991): 100–105. http://dx.doi.org/10.1115/1.2906515.
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This paper is devoted to the analyses and optimization of simple and sophisticated cycles, particularly for various gas turbine engines and aero-engines (including the scramjet engine) to achieve maximum performance. The optimization of such criteria as thermal efficiency, specific output, and total performance for gas turbine engines, and overall efficiency, nondimensional thrust, and specific impulse for aero-engines has been performed by the optimization procedure with the multiplier method. Comparison of results with analytical solutions establishes the validity of the optimization procedure.
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Vetrov, A. N., and A. G. Kucher. "Estimate of remaining life of blades in aircraft gas turbines from accumulated creep strain." Strength of Materials 25, no. 1 (January 1993): 42–47. http://dx.doi.org/10.1007/bf00767734.
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Zaretsky, E. V. "Ceramic Bearings for Use in Gas Turbine Engines." Journal of Engineering for Gas Turbines and Power 111, no. 1 (January 1, 1989): 146–54. http://dx.doi.org/10.1115/1.3240213.
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Three decades of research by U.S. industry and government laboratories have produced a vast array of data related to the use of ceramic rolling-element bearings and bearing components for aircraft gas turbine engines. Materials such as alumina, silicon carbide, titanium carbide, silicon nitride, and a crystallized glass ceramic have been investigated. Rolling-element endurance tests and analysis of full-complement bearings have been performed. Materials and bearing design methods have improved continuously over the years. This paper reviews a wide range of data and analyses with emphasis on how early NASA contributions as well as more recent data can enable the engineer or metallurgist to determine just where ceramic bearings are most applicable for gas turbines.
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Wicks, Frank. "Mercury and Steam." Mechanical Engineering 137, no. 07 (July 1, 2015): 40–45. http://dx.doi.org/10.1115/1.2015-jul-2.
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This article is a memoir of William Emmet, a General Electric engineer in the field of combined-cycle gas turbine power plants. Despite the odds against the idea, several combined mercury and steam plants were built and achieved the promised high efficiency. This improbable achievement can be credited to a General Electric engineer named William Emmet. While Emmet’s early experience had been with direct current, he recognized the benefits and challenges of alternating current. The fuel efficiency of Emmet’s mercury dual cycle was eventually made obsolete by increased steam plant efficiencies from higher pressures and reheating the steam. Emmet’s contributions today are mostly hidden improvements in rotating electric machinery and apparatus. In contrast, his success in developing the impulse turbine helped create a technology base of engineers and manufacturing. It positioned General Electric to take the lead in turbochargers for piston aircraft engines, and later global leadership in aircraft jet engines and land-based gas turbines for electricity and industry.
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Spinelli, Andrea, Gustavo Pedro Krupa, Timoleon Kipouros, Boris Berseneff, and Sébastien Fiette. "Investigation of the operational flexibility of a regional hybrid-electric aircraft." Journal of Physics: Conference Series 2526, no. 1 (June 1, 2023): 012021. http://dx.doi.org/10.1088/1742-6596/2526/1/012021.
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Abstract The complexity of hybrid-electric aircraft propulsion systems is also characterized by the greater number of degrees of freedom of the energy management system, whose objective is to split the required power to fly the aircraft to the different available powertrains (i.e., gas turbines, electric motors, fuel cells, etc.). Typically, a single design mission is considered for assessing the performance of a hybrid-electric propulsion system, often with a simple constant split power between the batteries and gas turbine. A probabilistic set-based design space exploration methodology is used and allows us to study the effects of lifecycle analysis of the battery pack of a hybrid-electric 50-seater turboprop, while different mission scenarios are considered. Using this approach, it is possible to flexibly find multiple families of energy management strategies that can satisfy battery capacity requirements and the reduction of emissions simultaneously. Furthermore, the generated data can help the designers to understand the hierarchy of the requirements that drive the design of the propulsion system for a range of operating scenarios, with emphasis on the energy storage system. Hence, the airliners are offered enhanced operational flexibility of the aircraft for different and desirable mission profiles.
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Zahra, Nyimas Aljaniah, Sovian Aritonang, and Nugroho Adi Sasongko. "APPLICATION OF INCONEL 718 (IN718) FOR ADVANCED ARMOR MATERIAL AND ITS POTENTIAL IN INDONESIA DEFENSE INDUSTRY." Jurnal Pertahanan: Media Informasi ttg Kajian & Strategi Pertahanan yang Mengedepankan Identity, Nasionalism & Integrity 8, no. 1 (April 30, 2022): 41. http://dx.doi.org/10.33172/jp.v8i1.1440.
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<div><p class="Els-history-head">Indonesia is the world's largest source of nickel ore, controlling 27 percent of the global nickel market. Because of its unique physicochemical properties, such as malleability, high-temperature stability, strength, corrosion resistance, ductility, heat conductivity, and electrical conductivity, nickel is one of the most important metals in the industry. Nickel-based superalloys are commonly utilized to build hot-end components for aviation engines and gas turbines. The purpose of this study is to examine the use of Inconel 718 (IN718) for armor and its prospective development in Indonesia's military industry. The outcome demonstrates IN718's potential in the Indonesian defense industry, with the manufacturing of military aircraft gas turbines, submarines, military electric engines, and high-protection armor vehicles among its most prominent applications. Nickel may be recycled by using a nickel extraction technique like the liquid metal extraction-vacuum distillation (LME-VD), which produces no waste gas or solid and is environmentally beneficial. IN718's development is also by the government's goal of increasing the value-added of Indonesia's nickel production while minimizing environmental impact.</p></div>
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Han, Je-Chin. "Recent Studies in Turbine Blade Cooling." International Journal of Rotating Machinery 10, no. 6 (2004): 443–57. http://dx.doi.org/10.1155/s1023621x04000442.
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Gas turbines are used extensively for aircraft propulsion, land-based power generation, and industrial applications. Developments in turbine cooling technology play a critical role in increasing the thermal efficiency and power output of advanced gas turbines. Gas turbine blades are cooled internally by passing the coolant through several rib-enhanced serpentine passages to remove heat conducted from the outside surface. External cooling of turbine blades by film cooling is achieved by injecting relatively cooler air from the internal coolant passages out of the blade surface in order to form a protective layer between the blade surface and hot gas-path flow. For internal cooling, this presentation focuses on the effect of rotation on rotor blade coolant passage heat transfer with rib turbulators and impinging jets. The computational flow and heat transfer results are also presented and compared to experimental data using the RANS method with various turbulence models such as k-ε, and second-moment closure models. This presentation includes unsteady high free-stream turbulence effects on film cooling performance with a discussion of detailed heat transfer coef- ficient and film-cooling effectiveness distributions for standard and shaped film-hole geometry using the newly developed transient liquid crystal image method.
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Sylvestre, R. A., and R. J. Dupuis. "The Evolution of Marine Gas Turbine Controls." Journal of Engineering for Gas Turbines and Power 112, no. 2 (April 1, 1990): 176–81. http://dx.doi.org/10.1115/1.2906158.
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The background and evolution of gas turbine fuel controls is examined in this paper from a Naval perspective. The initial application of aeroderivative gas turbines to Navy ships utilized the engine’s existing aircraft fuel controls, which were coupled to the ship’s hydropneumatic machinery control system. These engines were adapted to Naval requirements by including engine specific functions. The evolution of Naval gas turbine controllers first to analog electronic, and more recently, to distributed digital controls, has increased the system complexity and added a number of levels of machinery protection. The design of a specific electronic control module is used to illustrate the current state of the technology. The paper concludes with a discussion of the further need to address the issues of fuel handling, metering and control in Navy ships with particular emphasis on integration in the marine environment.
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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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Khomylyev, Sergiy, Igor Kravchenko, and Andriy Popuga. "Approach to the Selection of Optimal Characteristics for Low Pressure Turbines Using a Single Gas Generator." NTU "KhPI" Bulletin: Power and heat engineering processes and equipment, no. 3-4 (December 28, 2022): 5–10. http://dx.doi.org/10.20998/2078-774x.2022.03.01.
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An approach to the conceptual design of the low pressure turbine for the aviation turbopropeller engine has been shown. The engine is created on the basis of the single gas generator for the two-engine power plant intended for the average transport aircraft. This approach is of great interest because in addition to the efficiency factor, the mass of the designed turbine, the fuel mass and the number of aerodynamic profile were used as optimal design criteria. The designed turbine includes the two stages and the interturbine transition channel of a diffuser type arranged in front of them. Consideration was given to the four flow parts of the turbine that differ by the diameter and the height selected in the preset limitation range. The gas dynamic efficiency of the interturbine transition channel, gas dynamic efficiency of the after-turbine channel, the strength of the turbine blade of the last stage were taken as the limitations. The dependences of the efficiency factor, the turbine mass and the number of turbine blades on the turbine aerodynamic load factor were obtained for the four turbine options. The turbine efficiency factor was determined using our own method of one-dimensional gas-dynamic computation. The fuel flow rate was determined using the mathematical engine model. The turbine mass was determined using the parametric method as a function of the aerodynamic load factor and the turbine flow rate factor. The number of aerodynamic profiles was defined using the Zweifel parameter. It was shown that the use of heavy loaded and less loaded low pressure turbines can reduce the take-off weight of the aircraft in spite of an increased fuel flow rate.
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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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Guellouh, Noureddine, Zoltán Szamosi, and Zoltán Siménfalvi. "Combustors with Low Emission Levels for Aero Gas Turbine Engines." International Journal of Engineering and Management Sciences 4, no. 1 (March 3, 2019): 503–14. http://dx.doi.org/10.21791/ijems.2019.1.62.
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The aircrafts are responsible for emitting several types of pollutants, especially the pollutants in the form of NOX, CO2, CO, UHC, SOX and Particulate Matter PM (smoke/soot). The impact of aviation emissions on the global is well known, where these emissions modify the chemical and microphysical properties of the atmosphere resulting in changes of earth’s climate system, which can ultimate in critical changes in our planet fragile ecosystem, also the pollutants produced by aircraft engines cause many health problems. This is why the International Civil Aviation Organisation (ICAO) is seriously seeking to control the emission levels by issuing new standards during the successive meetings of the Committee on Aviation Environmental Protection CAEP (CAEP/01 in 1986, CAEP/2, CAEP/4, CAEP/6, CAEP/8, etc). The new regulations include more stringent standards aimed to reduce emission levels, this led to increased interest in low emission technologies. In this paper, a comprehensive review of low emissions combustion technologies for modern aero gas turbines is represented. The current low emission technologies include the high Technologies Readiness Level (TRL) including RQL, TAPS, DAC and LDI. Also, there are advanced technologies at lower TRL including LPP, ASC and VGC.
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Lawen, J. L., S. J. Calabrese, and O. S. Dinc. "Wear Resistance of Super Alloys at Elevated Temperatures." Journal of Tribology 120, no. 2 (April 1, 1998): 339–44. http://dx.doi.org/10.1115/1.2834432.
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This paper provides the results of an extensive sliding wear testing program to evaluate wear resistance of several material couples currently used for high temperature applications such as ground based gas turbines and aircraft engines. Nickel and cobalt base superalloys and iron base stainless steels were tested in different combinations, and their wear rates compared to determine optimal wear resistance. The results show that an alloy’s wear resistance is highly dependent on operating temperature and its coupling with another material. The influences of friction, hardness, and oxide formation on the alloy’s wear resistance are also presented and discussed.
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Ravibharath, R., K. Devakumaran, and V. Muthupandi. "Studies on Susceptibility of Alloy 617 to Solidification Cracking." Materials Science Forum 969 (August 2019): 34–40. http://dx.doi.org/10.4028/www.scientific.net/msf.969.34.
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Ni based super alloy 617 is widely used in transition liners in both aircraft and land-based gas turbines, power plant applications because of its high temperature strength, oxidation resistance and creep properties. Ni based alloys are highly susceptible to hot cracking like solidification and liquation racking issues. In this present work, the susceptibility of alloy 617 to solidification cracking is studied based on the varestraint test. Results of this weldability test proved that in addition to the solidification cracking susceptibility alloy 617 is prone to liquation cracking also. Keywords: Varestraint test, Alloy 617, Solidification cracking, Liquidation cracking.
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Dimos, Dimitrios, and Stefanie de Graaf. "Overview of safety challenges associated with integration of hydrogen-based propulsion systems for climate neutral aviation." Journal of Physics: Conference Series 2716, no. 1 (March 1, 2024): 012001. http://dx.doi.org/10.1088/1742-6596/2716/1/012001.
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Abstract Electrification through hydrogen-based fuel cells as well as hydrogen combustion in gas turbines is a key strategy in aviation for achieving substantial reduction of emissions. However, this transition presents multifaceted challenges. Besides the development and improvement of technologies required for such hydrogen-fuelled aero engines, the safety of hydrogen storage and distribution systems on aircraft is paramount. Challenges associated with hydrogen in terms of its material properties, the design and selection of components for the conditioning and distribution, as well as the system design are being presented and discussed in this work. This includes the consideration of high diffusivity, flammability and reactivity of hydrogen and the consequences of these traits: hydrogen embrittlement, hydrogen-induced cracking and leakage, for instance. The challenges elaborated in this work are pertinent to both hydrogen fuel cell-based propulsion systems and hydrogen combusting gas turbines. Design considerations were derived and are being outlined in this work. These are transferable to applications in other industries such as automotive and stationary power plants. The need for novel rigorous safety protocols to enable a sustainable future in aviation is being highlighted.
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MacPhail, D. C., A. S. Jackson, and E. S. Moore. "Machinery arrangements for small Vtol transport aircraft." Aeronautical Journal 97, no. 963 (March 1993): 101–10. http://dx.doi.org/10.1017/s0001924000025185.
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SummaryAircraft plying between urban and outlying communities usually enjoy a runway with noise restrictions at the urban end and perhaps little to land on at the other end, but with no objection to noisy operation. The existence of this situation in northern Canada persuaded the National Research Council to embark — some thirty years ago — on an investigation of powered lift possibilities, with strong support from the trunk and regional airlines, the charter and helicopter operators, and various manufacturers.From a number of generic lift-propulsion arrangements examined in greater or lesser detail, a selection are described here in increasing order of what the certifying authorities call “damage tolerance” or reduced dependence on “critical parts”. Freedom from demands for hovering endurance and quietness, combined with emphasis on small aircraft, offered encouragement to attack what is otherwise a very difficult task. Of the alternatives, only one, which incorporated transverse axis fans and the light weight gas turbines now available, emerged as a potentially satisfactory choice for small rugged transport aircraft.The project was discontinued because of pressure of other work, but is recounted here in case others may discern wider market possibilities. A small Vtol aircraft should, if successful, be a useful precursor to sophisticated airliners capable of taking off and landing without a run.
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Jonšta, Petr, Irena Vlčková, Zdenĕk Jonšta, and Božena Podhorná. "Materialographic Analysis of MAR M-247 Superalloy." Key Engineering Materials 647 (May 2015): 66–71. http://dx.doi.org/10.4028/www.scientific.net/kem.647.66.
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This paper presents the results of structural phase analysis of MAR-M247 superalloy. Analysis was performed at initial and in as casted state after various type of solution annealing in the range 900 °C to 1240 °C with cooling in water. Presented polycrystalline alloy is heat resisting nickel superalloy, especially usable for highly strained components in the industry producing stationary gas turbines and aircraft engines. Analysis was performed using of a Quanta FEG 450 scanning electron microscope with micro-analytic system Trident APEX-4 which have identified presented minor phase. Attention was also paid to its eventual changes after different type of solution annealing.
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Błachnio, Józef. "The Effect of High Temperature on the Degradation of Heat-Resistant and High-Temperature Alloys." Solid State Phenomena 147-149 (January 2009): 744–51. http://dx.doi.org/10.4028/www.scientific.net/ssp.147-149.744.
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Heat-resistant and high-temperature materials are used to manufacture components, devices, and systems operated at high temperatures, i.e. under severe heat loads. Gas turbines used in the power industry, the traction, marine, and aircraft engines, the aerospace technology, etc. are good examples of such systems. Generally, as the temperature increases, the mechanical strength of materials decreases. While making such materials, there is a tendency to keep possibly low thermal weakening. In the course of operating gas turbines, various kinds of failures/defects/ damages may occur to components thereof, in particular, to blades. Predominating failures/damages are those attributable to the material overheating and thermal fatigue, all of them resulting in the loss of mechanical strength. The paper has been intended to present findings on changes in the microstructure of blades made of nickel-base alloy due to high temperature. The material gets overheated, which results in the deterioration of the microstructure’s condition. The material being in such condition presents low high-temperature creep resistance. Any component, within which such an effect occurs, is exposed to a failure/damage usually resulting in the malfunctioning of the turbine, and sometimes (as with aero-engines) in a fatal accident. Failures/damages of this kind always need major repairs, which are very expensive.