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Journal articles on the topic 'Turbine engines materials'
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1
Pyatov, I. S., O. V. Shiboev, V. G. Buzinov, A. R. Makarov, A. V. Kostyukov, V. N. Posedko, L. A. Finkelberg, and A. N. Kostyuchenkov. "Carbon materials for parts of gas-turbine engines and internal combustion engines, problems and prospects." Izvestiya MGTU MAMI 8, no. 4-1 (February 20, 2014): 55–60. http://dx.doi.org/10.17816/2074-0530-67679.
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The paper presents the results of application of carbon-containing material "KARBUL" for manufacturing for internal combustion engine pistons, the technology of piston manufacturing of material "KARBUL". The authors describe the prospects for use of "KARBUL" material for small-size gas turbine engines.
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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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Kharlina, Ekaterina. "LOW-EMISSION COMBUSTION CHAMBERS AND COOLING SYSTEMS." Perm National Research Polytechnic University Aerospace Engineering Bulletin, no. 70 (2022): 29–40. http://dx.doi.org/10.15593/2224-9982/2022.70.03.
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A modern gas turbine engine must meet a large list of requirements that are included in the parameters, resource and per-formance indicators. To increase the service life of a gas turbine engine at elevated temperatures of the gas flow, it is expendable to use thermal barrier protection on explosive structural materials. Cyclic tests of materials and thermal barrier coatings of gas tur-bine engines at temperatures above 1500 ºС are proposed to be carried out on a stand in which a hot gas flow is generated by an air-methane burner. In order to reduce the emission standards for nitrogen and carbon oxides, it is necessary to develop and use in stationary gas turbine engines fundamentally new technologies for organizing combustion and, as a result, designs of combustion chambers. From a detailed analysis of the current requirements, it follows that the newly designed low-emission combustion chamber for advanced gas turbine engines and installations should be accompanied by an increase in gas temperature by 200–300 K, an increase in the durability of the flame tube by 3–4 times, with a twofold decrease in the proportion of air for cooling the walls, a twofold or more reduction in the emission of harmful substances. In this article, heat-resistant coatings of structural elements of gas turbines are considered. The concepts of low-emission fuel combustion are described by organizing the working process according to the "DLE" - Dry Low Emission scheme. As an alter-native method for organizing low-emission combustion, stoichiometric combustion is proposed, which also makes it possible to provide the required temperature of the gas jet. A review of low-emission combustion chambers has been carried out. The existing methods of cooling the combustion chambers of gas turbine and liquid rocket engines are described. The analysis of the collected information made it possible to determine the concept of designing a high-temperature air-methane burner.
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Danko, Gene A. "By Leaps and Bounds: The Realization of Jet Propulsion through Innovative Materials and Design." Key Engineering Materials 380 (March 2008): 135–46. http://dx.doi.org/10.4028/www.scientific.net/kem.380.135.
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Innovations in gas turbine engine design and materials are tracked from the earliest days of functional engines to the present. Materials and design are shown to be mutually interdependent, driving engine capability to unprecedented levels of performance with each succeeding product generation.
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Zhong, Yan, Liangyu Chen, Xinyu Wang, Lei Zhao, Haoxi Bai, Bing Han, Shengzhen Cheng, and Jingbo Luo. "Angle-Regulating Rule of Guide Vanes of Variable Geometry Turbine Adjusting Mechanism." Applied Sciences 13, no. 11 (May 23, 2023): 6357. http://dx.doi.org/10.3390/app13116357.
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In recent years, more and more attention has been paid to research on variable geometry turbine engines with the increasing requirement of engine performance. Variable geometry turbine technology can significantly improve the operating performance of aero engines. Adjusting the working angle of the turbine guide vane can change the thermodynamic cycle of the engine operation, so that the turbine can respond to different engine operating conditions. Variable geometry turbines work in harsh environments. Therefore, the design of the variable geometry turbine needs to consider the effect of thermal deformations of the mechanism on operational stability. There are few research studies on variable geometry turbine adjusting mechanisms. This paper established the numerical calculation models of two adjusting mechanisms by integrating fluid mechanics, heat transfer, and dynamic theories, which are paddle and push–pull rod mechanisms. The models were applied to study the effects of components’ thermal deformations and flexible bodies on the motion characteristics of the adjusting mechanism. Furthermore, the performance of the two adjusting mechanisms was compared. The calculation results show that the paddle rod adjusting mechanism can accurately adjust the angles of guide vanes. The paddle rod adjusting mechanism has a larger driving stroke and smaller driving force than the push–pull rod adjusting mechanism. The paddle adjustment mechanism was better suited to the operational requirements of the variable geometry turbine. The research results of this paper are relevant to the design of variable geometry turbine regulation structures.
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OPARA, Tadeusz. "History and future of turbine aircraft engines." Combustion Engines 127, no. 4 (November 1, 2006): 3–18. http://dx.doi.org/10.19206/ce-117335.
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This paper discusses stages of development of air propulsion from piston engines up to three-rotor turbine ones. Limitations in speed and altitude of flight, caused by traditional system of a piston engine and an airscrew, became an impulse to conduct research on jet propulsion. Accomplishments of the designers of the first jet-propelled engines: F. Whitle and H. von Ohain are a reflection of rivalry in this field. In the second half of the 20th centur y turbine propulsion (turbojet, turboprop and helicopter engines) dominated air force and civil aviation. In 1960 the age of turbofans began, owing to better operating properties and electronic and digital systems of automatic regulation. Further development of turbine engines is connected with application of qualitatively new materials (particularly composites), optimization of the shape of compressor and turbine blades and technologies of their production. The paper discusses design changes decreasing the destructive effects of foreign matter suction and indicates the possibility of increasing the maneuverability of airplanes by thrust vectoring. Finally, development prospects of turbine propulsion are analyzed.
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Meetham, G. W. "High temperature materials in gas turbine engines." Materials & Design 9, no. 4 (July 1988): 213–19. http://dx.doi.org/10.1016/0261-3069(88)90033-7.
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Easley, M. L., and J. R. Smyth. "Ceramic Gas Turbine Technology Development." Journal of Engineering for Gas Turbines and Power 117, no. 4 (October 1, 1995): 783–91. http://dx.doi.org/10.1115/1.2815465.
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AlliedSignal Engines is addressing critical concerns slowing the commercialization of structural ceramics in gas turbine engines. These issues include ceramic component reliability, commitment of ceramic suppliers to support production needs, and refinement of ceramic design technologies. The stated goals of the current program are to develop and demonstrate structural ceramic technology that has the potential for extended operation in a gas turbine environment by incorporation in an auxiliary power unit (APU) to support automotive gas turbine development. AlliedSignal Engines changed the ATTAP ceramic engine test bed from the AGT101 automotive engine to the 331-200[CT] APU. The 331-200[CT] first-stage turbine nozzle segments and blades were redesigned using ceramic materials, employing design methods developed during the earlier DOE/NASA-funded Advanced Gas Turbine (AGT) and the ATTAP programs. The ceramic design technologies under development in the present program include design methods for improved resistance to impact and contact damage, assessment of the effects of oxidation and corrosion on ceramic component life, and assessment of the effectiveness of nondestructive evaluation (NDE) and proof testing methods to reliably identify ceramic parts having critical flaws. AlliedSignal made progress in these activities during 1993 ATTAP efforts. Ceramic parts for the 331-200[CT] engine have been fabricated and evaluated in component tests, to verify the design characteristics and assure structural integrity prior to full-up engine testing. Engine testing is currently under way. The work summarized in this paper was funded by the U.S. Dept. of Energy (DOE) Office of Transportation Technologies and administered by NASA-Lewis Research Center, under Contract No. DEN3-335.
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Sadowski, Tomasz, and Przemysław Golewski. "The Analysis of Heat Transfer and Thermal Stresses in Thermal Barrier Coatings under Exploitation." Defect and Diffusion Forum 326-328 (April 2012): 530–35. http://dx.doi.org/10.4028/www.scientific.net/ddf.326-328.530.
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Effectiveness of internal combustion turbines in aero-engines is limited by comparatively low temperature of exhaust gas at the entry to turbine of the engine. A thermal efficiency and other capacities of turbine strongly depend on the ratio of the highest to the lowest temperature of a working medium. Continuous endeavour to increase the thermal resistance of engine elements requires, apart from laboratory investigations, also numerical studies in 3D of different aero-engine parts. In the present work, the effectiveness of the protection of turbine blades by thermal barrier coating and internal cooling under thermal shock cooling was analysed numerically using the ABAQUS code. The phenomenon of heating the blade from temperature of combustion gases was studied. This investigation was preceded by the CFD analysis in the ANSYS Fluent program which allows for calculation of the temperature of combustion gases. The analysis was conducted for different levels of the shock temperature, different thickness of applied TBC, produced from different kinds of materials.
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Maniam, Kranthi Kumar, and Shiladitya Paul. "Progress in Novel Electrodeposited Bond Coats for Thermal Barrier Coating Systems." Materials 14, no. 15 (July 28, 2021): 4214. http://dx.doi.org/10.3390/ma14154214.
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The increased demand for high performance gas turbine engines has resulted in a continuous search for new base materials and coatings. With the significant developments in nickel-based superalloys, the quest for developments related to thermal barrier coating (TBC) systems is increasing rapidly and is considered a key area of research. Of key importance are the processing routes that can provide the required coating properties when applied on engine components with complex shapes, such as turbine vanes, blades, etc. Despite significant research and development in the coating systems, the scope of electrodeposition as a potential alternative to the conventional methods of producing bond coats has only been realised to a limited extent. Additionally, their effectiveness in prolonging the alloys’ lifetime is not well understood. This review summarises the work on electrodeposition as a coating development method for application in high temperature alloys for gas turbine engines and discusses the progress in the coatings that combine electrodeposition and other processes to achieve desired bond coats. The overall aim of this review is to emphasise the role of electrodeposition as a potential cost-effective alternative to produce bond coats. Besides, the developments in the electrodeposition of aluminium from ionic liquids for potential applications in gas turbines and the nuclear sector, as well as cost considerations and future challenges, are reviewed with the crucial raw materials’ current and future savings scenarios in mind.
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Epstein, Alan H. "Millimeter-Scale, Micro-Electro-Mechanical Systems Gas Turbine Engines." Journal of Engineering for Gas Turbines and Power 126, no. 2 (April 1, 2004): 205–26. http://dx.doi.org/10.1115/1.1739245.
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The confluence of market demand for greatly improved compact power sources for portable electronics with the rapidly expanding capability of micromachining technology has made feasible the development of gas turbines in the millimeter-size range. With airfoil spans measured in 100’s of microns rather than meters, these “microengines” have about 1 millionth the air flow of large gas turbines and thus should produce about one millionth the power, 10–100 W. Based on semiconductor industry-derived processing of materials such as silicon and silicon carbide to submicron accuracy, such devices are known as micro-electro-mechanical systems (MEMS). Current millimeter-scale designs use centrifugal turbomachinery with pressure ratios in the range of 2:1 to 4:1 and turbine inlet temperatures of 1200–1600 K. The projected performance of these engines are on a par with gas turbines of the 1940s. The thermodynamics of MEMS gas turbines are the same as those for large engines but the mechanics differ due to scaling considerations and manufacturing constraints. The principal challenge is to arrive at a design which meets the thermodynamic and component functional requirements while staying within the realm of realizable micromachining technology. This paper reviews the state of the art of millimeter-size gas turbine engines, including system design and integration, manufacturing, materials, component design, accessories, applications, and economics. It discusses the underlying technical issues, reviews current design approaches, and discusses future development and applications.
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Hussain*, Moaz, P. Deepak Kumar, S. R. Arun, Vismaya, and P. Hari Siva. "Development of Novel Computer Program for Cycle Analysis of Turbojet Engine." International Journal of Innovative Technology and Exploring Engineering 9, no. 4 (February 28, 2020): 1872–78. http://dx.doi.org/10.35940/ijrte.d1601.018520.
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A method to simulate the gas turbine cycle and performance is developed. This paper intent to describe a digital computer code to make it useful for other researchers. This program is written in Python language for analyzing the steady-state, parametric cycle performance of turbojet engines. This can be used to analyze one- and two-spool turbojet engines without any modification to the basic program. The influence of initial parameters, component characteristics and flight condition on performance characteristics of gas turbine during operation are shown. The program results are compared and validated with those from an existing GSP (Gas Turbine Simulation Program) software. The major advantage of this new method is that it frees the programmer from having to minimize the number of equations which require iterative solution. As a result, some of the approximations normally used in engine simulations can be eliminated. The outcomes of this analysis form a strong base for further analysis to predict the performance of the gas turbine engine with reasonable accuracy for design and fabrication of gas turbine engines using this performance code.
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Dologlonyan, Andrey V., Dmitriy S. Strebkov, and Valeriy T. Matveenko. "Thermodynamic Characteristics of Hybrid Solar Microgas Turbine Plants under Tropical Climate." Elektrotekhnologii i elektrooborudovanie v APK 2, no. 43 (2021): 20–35. http://dx.doi.org/10.22314/2658-4859-2021-68-2-20-35.
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The article presents the results obtained during the study of the characteristics of hybrid solar micro-gas turbine units with an integrated parabolocylindrical solar collector. The efficiency of a hybrid solar gas turbine plant depends both on the efficiency of the solar collector and the location of its integration, and on the efficiency of the gas turbine engine. (Research purpose) The research purpose is in studying hybrid solar gas turbine installations based on a parabolocylindrical focusing solar collector in combination with micro-gas turbine engines of various configurations to determine the most suitable match. (Materials and methods) The article considers four basic schemes of gas turbine engines running on organic fuel, their parameters and optimization results. The article presents the main climatic parameters for the study of the focusing solar collector, as well as the parameters of the collector itself and the main dependencies that determine its efficiency and losses. The place of integration of the focusing solar collector into the gas turbine plant was described and justified. (Results and discussion) Hybrid solar micro-gas turbine installations based on micro-gas turbine engines of a simple cycle, a simple cycle with heat recovery, a simple cycle with a turbocharger utilizer, a simple cycle with a turbocharger utilizer and heat recovery for tropical climate conditions were studied on the example of Abu Dhabi. (Conclusions) The most suitable configuration of micro-gas turbine engines for integrating a focusing solar collector is a combination of a simple cycle with a turbocharger utilizer and regeneration. The combination of micro-gas turbine engines of a simple cycle with a turbocharger heat recovery and heat recovery with an integrated focusing solar collector can relatively increase the average annual efficiency of fuel consumption of such installations in a tropical climate by 10-35 percent or more, while maintaining cogeneration capabilities.
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Pismennyi, V. L. "Methods and techniques used in increasing gas temperature in front of the gas turbine engine turbine." Proceedings of Higher Educational Institutions. Маchine Building, no. 6 (759) (June 2023): 108–18. http://dx.doi.org/10.18698/0536-1044-2023-6-108-118.
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The paper presents methods and techniques used in increasing gas temperature in front of the turbine blades of the gas turbine engine making it possible in the aggregate to reach the gas temperature of 2300 K. Gas turbine blades made on the basis of the best nickel alloys could operate for a long time without cooling at the temperature of not more than 1300 K. Convective-film cooling today appears to be the most effective method of air cooling the blades, due to which (in combination with the heat-shielding coatings) gas temperature of 2000 K is reached in the fifth-generation gas turbine engines. Significant increase in the efficiency of the turbine blades internal cooling (convective, convective-film, porous) is obtained with using the external cooling, i.e. decreasing the cooling air temperature by the cooling resource of the external environment: atmospheric air (secondary air), water and fuel. External cooling when using the convective-film cooling makes it possible to increase gas temperature in front of the turbine blades by 0.6 ... 1.5 K for each degree in the cooling air temperature decrease. A circulating heat exchanger is proposed, which lowers the cooling air temperature almost to the ambient temperature making it possible in combination with the known methods and techniques for increasing the gas temperature (heat-resistant materials, heat-shielding coatings, convective-film cooling) to increase gas temperature in front of the turbine blades by 300...400 K and bring it up to at least 2300 K. This would allow today to start creating stoichiometric and hyperforced gas turbine engines and to increase the bypass turbojet engines efficiency up to 45%. Air-liquid cooling is a variation of the turbine blades external cooling. The possibility (technical solutions were patented) of introducing the air-liquid cooling in gas turbine engines at the high flight speeds, including the turbojet engines, was studied.
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Łęczycki, Krzysztof. "Selected issues of materials testing of rolling bearings adapted to work in elevated temperatures." Transportation Overview - Przeglad Komunikacyjny 2018, no. 9 (September 1, 2018): 28–39. http://dx.doi.org/10.35117/a_eng_18_09_04.
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Rolling bearings are crucial component of aviation turbine engines. Bearing failure may, in worst case, lead to an engine failure and aircraft disaster. Therefore, investigation of their causes and subsequent risk factors elimination are of utmost importance. In the present study, selected materials testing issues of two rolling bearings from light rotorcraft turbine enignes failures (in accidents of 2016 & 2017) are discussed. Results of macroscopic, hardness tests, microstructure and chemical assay are presented. The obtained data are compared with results of previous studies on the subject.
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Gell, Maurice. "Applying nanostructured materials to future gas turbine engines." JOM 46, no. 10 (October 1994): 30–34. http://dx.doi.org/10.1007/bf03222605.
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Yun, Jung Yeul, Shun Myung Shin, Dong Won Lee, Jong Nam Kim, and Jei Pil Wang. "Fabrication of Fe-36Ni Alloy Powder from its Scrap." Advanced Materials Research 747 (August 2013): 619–22. http://dx.doi.org/10.4028/www.scientific.net/amr.747.619.
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Ni-based superalloys are used extensively in the hot section of gas turbine engines owing to their inherent elevated temperature strength and creep resistance. As such, aircraft engine manufactures are continually striving to push the envelope of the capabilities of such high temperature structure materials in order to increase both engine performance and efficiency [1,2].
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Velidi, Gurunadh, and Chun Sang Yoo. "A Review on Flame Stabilization Technologies for UAV Engine Micro-Meso Scale Combustors: Progress and Challenges." Energies 16, no. 9 (May 8, 2023): 3968. http://dx.doi.org/10.3390/en16093968.
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Unmanned aerial vehicles (UAV)s have unique requirements that demand engines with high power-to-weight ratios, fuel efficiency, and reliability. As such, combustion engines used in UAVs are specialized to meet these requirements. There are several types of combustion engines used in UAVs, including reciprocating engines, turbine engines, and Wankel engines. Recent advancements in engine design, such as the use of ceramic materials and microscale combustion, have the potential to enhance engine performance and durability. This article explores the potential use of combustion-based engines, particularly microjet engines, as an alternative to electrically powered unmanned aerial vehicle (UAV) systems. It provides a review of recent developments in UAV engines and micro combustors, as well as studies on flame stabilization techniques aimed at enhancing engine performance. Heat recirculation methods have been proposed to minimize heat loss to the combustor walls. It has been demonstrated that employing both bluff-body stabilization and heat recirculation methods in narrow channels can significantly improve combustion efficiency. The combination of flame stabilization and heat recirculation methods has been observed to significantly improve the performance of micro and mesoscale combustors. As a result, these technologies hold great promise for enhancing the performance of UAV engines.
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Kool, G. A. "Current and future materials in advanced gas turbine engines." Journal of Thermal Spray Technology 5, no. 1 (March 1996): 31–34. http://dx.doi.org/10.1007/bf02647514.
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Gell, Maurice. "The potential for nanostructured materials in gas turbine engines." Nanostructured Materials 6, no. 5-8 (January 1995): 997–1000. http://dx.doi.org/10.1016/0965-9773(95)00230-8.
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Szczepankowski, Andrzej, Janusz Szymczak, and Jaroslaw Spychała. "Operating Degradations of Air Turbine Scoops of Turbo-Engines." Solid State Phenomena 147-149 (January 2009): 524–29. http://dx.doi.org/10.4028/www.scientific.net/ssp.147-149.524.
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The paper presents various types of turbine scoops damages that are being found in the operating process of air turbine engines (TSO). When dividing them, having in mind a genesis of their origin, a special attention has been paid to corrosion and high-temperature erosion, often being a reason for destruction of the entire unit. The damages hereto described have been illustrated with examples collected during endoscope surveys of TSO internal spaces or their post-failure disassembly. The summary points out to the ways and directions of works aiming at early detection of TSO turbines units damages, and thus at improvement of their operating safety.
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Simic, Marko, Ana Alil, Sanja Martinovic, Milica Vlahovic, Aleksandar Savic, and Tatjana Volkov-Husovic. "High temperature materials: properties, demands and applications." Chemical Industry 74, no. 4 (2020): 273–84. http://dx.doi.org/10.2298/hemind200421019s.
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High-temperature materials are used in a wide range of industries and applications such as gas turbine engines for aircrafts, power and nuclear power plants, different types of furnaces, including blast furnaces, some fuel cells, industrial gas turbines, different types of reactors, engines, electronic and lighting devices, and many others. Demands for high-temperature materials are becoming more and more challenging every year. To perform efficiently, effectively and at the same time to be economically viable, the materials used at high temperatures must have certain characteristics that are particularly expected for applying under such extreme conditions, for example, the strength and thermal resistance. In the present review, some important requirements that should be satisfied by high temperature materials will be discussed. Furthermore, the focus is put on refractory concretes, ceramics, intermetallic alloys, and composites as four different categories of these materials, which are also considered in respect to possibilities to overcome some of the current challenges.
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Bewlay, B. P., M. Weimer, T. Kelly, A. Suzuki, and P. R. Subramanian. "The Science, Technology, and Implementation of TiAl Alloys in Commercial Aircraft Engines." MRS Proceedings 1516 (2013): 49–58. http://dx.doi.org/10.1557/opl.2013.44.
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ABSTRACTThe present article will describe the science and technology of titanium aluminide (TiAl) alloys and the engineering development of TiAl for commercial aircraft engine applications. The GEnxTM engine is the first commercial aircraft engine that is flying titanium aluminide (alloy 4822) blades and it represents a major advance in propulsion efficiency, realizing a 20% reduction in fuel consumption, a 50% reduction in noise, and an 80% reduction in NOx emissions compared with prior engines in its class. The GEnxTM uses the latest materials and design processes to reduce weight, improve performance, and reduce maintenance costs.GE’s TiAl low-pressure turbine blade production status will be discussed along with the history of implementation. In 2006, GE began to explore near net shape casting as an alternative to the initial overstock conventional gravity casting plus machining approach. To date, more than 40,000 TiAl low-pressure turbine blades have been manufactured for the GEnxTM 1B (Boeing 787) and the GEnxTM 2B (Boeing 747-8) applications. The implementation of TiAl in other GE and non-GE engines will also be discussed.
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Winstone, M. R., A. Partridge, and J. W. Brooks. "The contribution of advanced high-temperature materials to future aero-engines." Proceedings of the Institution of Mechanical Engineers, Part L: Journal of Materials: Design and Applications 215, no. 2 (April 1, 2001): 63–73. http://dx.doi.org/10.1177/146442070121500201.
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Improvements in the performance and efficiency of gas turbine engines have been intimately linked to the development of materials technologies for the high-temperature components. This paper reviews some of the recent research that will ensure that the engines for the next generation of aircraft deliver world class performance at an affordable cost.
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Kim, J., M. G. Dunn, A. J. Baran, D. P. Wade, and E. L. Tremba. "Deposition of Volcanic Materials in the Hot Sections of Two Gas Turbine Engines." Journal of Engineering for Gas Turbines and Power 115, no. 3 (July 1, 1993): 641–51. http://dx.doi.org/10.1115/1.2906754.
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This paper reports the results of a series of tests designed to determine the melting and subsequent deposition behavior of volcanic ash cloud materials in modern gas turbine engine combustors and high-pressure turbine vanes. The specific materials tested were Mt. St. Helens ash and a soil blend containing volcanic ash (black scoria) from Twin Mountain, NM. Hot section test systems were built using actual engine combustors, fuel nozzles, ignitors, and high-pressure turbine vanes from an Allison T56 engine can-type combustor and a more modern Pratt and Whitney F-100 engine annular-type combustor. A rather large turbine inlet temperature range can be achieved using these two combustors. The deposition behavior of volcanic materials as well as some of the parameters that govern whether or not these volcanic ash materials melt and are subsequently deposited are discussed.
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Bradshaw, Sean. "Next Generation Aircraft Propulsion: A Pratt & Whitney Approach." AM&P Technical Articles 181, no. 2 (March 1, 2023): 12–16. http://dx.doi.org/10.31399/asm.amp.2023-02.p012.
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Abstract Aircraft engines that minimize fuel consumption and operate on sustainable aviation fuels are key to meeting the air transportation sector’s commitment to net zero CO2 emissions by 2050. This article reports on work to implement sustainable propulsion technologies, including advanced gas turbine propulsion technologies, engines that are compatible with approved sustainable aviation fuels, hybrid-electric propulsion, and hydrogen propulsion. The article also describes efforts to reduce the environmental footprint related to condensation trails (contrails) from aircraft engine exhaust plumes.
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Shabarov, Alexander B., Alexander M. Moiseev, Mikhail S. Belov, and Andrey A. Achimov. "INFORMATION SYSTEM OF THE TEST BENCH FOR DRIVING GAS TURBINE ENGINES." Tyumen State University Herald. Physical and Mathematical Modeling. Oil, Gas, Energy 6, no. 4 (2020): 28–47. http://dx.doi.org/10.21684/2411-7978-2020-6-4-28-47.
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This article studies the problem of determining the technical condition of drive and energetic gas turbine engines (GTE) during acceptance tests that have been repaired at a specialized enterprise. The following descriptions are given: of the bench for testing drive and energetic gas turbine engines; of the bench systems for monitoring and measurement, methods for conducting acceptance tests; of the evaluation the quality of the repaired engine based on its thermogasdynamics parameters; of the processing of measurement results obtained during acceptance tests. The materials of the system of differential (subassembly) diagnostics of GTE are generalized. The authors have considered the features of diagnostics of transient modes of GTE. The authors suggest the transition from the engine node to its elements as one of the ways to further improve the differential diagnostics, which has required developing the technique and system of pressure and temperature measurement at inlet and outlet of stage axial compressor. An algorithm for differential (element-by-element) engine diagnostics is described using the example of an axial compressor stage.
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Dong, Yiwei, Weiguo Yan, Tao Liao, Qianwen Ye, and Yancheng You. "Model characterization and mechanical property analysis of bimetallic functionally graded turbine discs." Mechanics & Industry 22 (2021): 4. http://dx.doi.org/10.1051/meca/2021001.
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In advanced propulsive systems, a turbine disc bears vast mechanical and thermal loads under its working conditions of high-temperature gradients and high rotational velocity.The complex working conditions of aero-engine turbine discs place stringent performance requirements on the materials used. With dual organizations and superior composite performances, bimetallic functionally graded turbine discs have become a focus in the research of high thrust-to-weight ratio aero-engines. To study the mechanical properties of new bimetallic functionally graded materials under service conditions, we propose a volumetric fraction expression and adjustable composition distribution parameters that are suitable for simulating the composition distribution of bimetallic functionally graded turbine discs. On this basis, a characterization model for functionally graded materials based on the analysis of the internal thermodynamic properties of bimetallic turbine discs is established. The thermodynamic properties and fatigue performances of functionally graded materials under service conditions are analysed. Mechanical property simulations of functionally graded turbine discs are performed using different composition distribution parameters, and reasonable ranges are determined for the various composition distribution parameters. The results show that bimetallic functionally graded turbine discs are suitable for high-stress-gradient and high-temperature-gradient environments with lower weights than those of current GH4169 alloy turbine discs.
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Wagner, Matthew J., Nelson H. Forster, Kenneth W Van Treuren, and David T. Gerardi. "Vapor Phase Lubrication for Expendable Gas Turbine Engines." Journal of Engineering for Gas Turbines and Power 122, no. 2 (January 3, 2000): 185–90. http://dx.doi.org/10.1115/1.483193.
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Vapor phase lubrication (VPL) is an emerging technology that is currently targeted for application in limited life, expendable engines. It has the potential to cut 90 percent of the cost and weight of the lubrication system, when compared to a conventional liquid lubricated system. VPL, is effective at much higher temperatures than conventional liquid lubrication (600°C versus 200°C), so considerably less cooling for the bearing is required, to the extent that the bearing materials often dictate the maximum upper temperature for its use. The hot no. 8 bearing and the cold no. 1 bearing of the T63 engine were used to evaluate the applicability of this technology to the expendable engine environment. The no. 8 bearing was a custom made hybrid with T15 steel races, silicon nitride balls, and a carbon–carbon composite cage; it was run for 10.7 h at a race temperature of 450°C at full power, without incident. Prior to engine tests, a bearing rig test of the no. 8 bearing demonstrated an 18.6 h life at a race temperature of 500°C at engine full power speed of 50,000 rpm. Cold bearing performance was tested with the standard no. 1 bearing, which consisted of 52100 steel races and balls, and a bronze cage; it was run for 7.5 h at a race temperature of 34°C at flight idle power, without incident. A self-contained lubricant misting system, running off compressor bleed air, provided lubricant at flow rates of 7–25 ml/h, depending on engine operating conditions. These tests have demonstrated for the first time that a single self-contained VPL system can provide adequate lubrication to both the hot and cold bearings for the required life of an expendable cruise missile engine. [S0742-4795(00)01302-2]
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Jeong, Jae Jun, HyungSoo Lee, Dae Won Yun, Hi Won Jeong, Young-Soo Yoo, Seong-Moon Seo, and Je Hyun Lee. "Analysis of a Single Crystal Solidification Process of an Ni-based Superalloy using a CAFE Model." Korean Journal of Metals and Materials 61, no. 2 (February 5, 2023): 126–36. http://dx.doi.org/10.3365/kjmm.2023.61.2.126.
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The efficiency of gas turbines depends on the gas turbine working temperature. Single crystal blades are being applied more often than equiaxed blades in gas turbine engines, to increase the turbine inlet temperature, resulting in enhanced turbine engine efficiency. Single crystal blades endure creep conditions at high temperature better than polycrystal blades because the single crystals do not include grain boundaries. The single crystal process is a breakthrough technology, however, production yield is relatively low compared with polycrystal, and their mechanical properties depend on the crystallographic orientation of the single crystals. In this study, a thermal simulation model, the 3D cellular automation-finite element (CA-FE), was used on the single crystal process with the Bridgman method. The simulation model was well expected, by analysis of the microstructure and EBSD, on the grain selection in the single crystal process. The evolution of single crystal grains was analyzed on process of grain selection in start block and spiral selector. Single crystal orientation was also investigated to determine the effect of nucleation density, forming in the initial stage of solidification.
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Brockmeyer, J. W. "Ceramic Matrix Composite Applications in Advanced Liquid Fuel Rocket Engine Turbomachinery." Journal of Engineering for Gas Turbines and Power 115, no. 1 (January 1, 1993): 58–63. http://dx.doi.org/10.1115/1.2906686.
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Hot gas path components of current generation, liquid fuel rocket engine turbopumps (T/P) are exposed to severe thermal shock, extremely high heat fluxes, corrosive atmospheres, and erosive flows. These conditions, combined with high operating stresses, are severely degrading to conventional materials. Advanced turbomachinery (T/M) applications will impose harsher demands on the turbine materials. These demands include higher turbine inlet temperature for improved performance and efficiency, lower density for improved thrust-to-weight ratio, and longer life for reduced maintenance of re-usable engines. Conventional materials are not expected to meet these demands, and fiber-reinforced ceramic matrix composites (FRCMC) have been identified as candidate materials for these applications. This paper summarizes rocket engine T/M needs, reviews the properties and capabilities of FRCMC, identifies candidate FRCMC materials and assesses their potential benefits, and summarizes the status of FRCMC component development with respect to advanced liquid fuel rocket engine T/M applications.
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Kuznetsov, N. D. "Advanced gas turbine engines and corrosion problems." Strength of Materials 25, no. 8 (August 1993): 610–18. http://dx.doi.org/10.1007/bf01151131.
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Abdollahzadeh Jamalabadi, Mohammad yaghoub. "Thermal radiation effects on creep behavior of the turbine blade." Multidiscipline Modeling in Materials and Structures 12, no. 2 (August 8, 2016): 291–314. http://dx.doi.org/10.1108/mmms-09-2015-0053.
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Purpose – The purpose of this paper is to find the time dependent thermal creep stress relaxation of a turbine blade and to investigate the effect thermal radiation of the adjacent turbine blades on the temperature distribution of turbine blade and creep relaxation. Design/methodology/approach – For this analysis, the creep flow behavior of Moly Ascoloy in operational temperature of gas turbine in full scale geometry is studied for various thermal radiation properties. The commercial software is used to pursue a coupled fields analysis for turbine blades in view of the structural force, materials kinematic hardening, and steady-state temperature field. Findings – During steady-state operation, the thermal stress was found to be decreasing, whereas by considering the thermal radiation this rate was noticed to increase slightly. Also by increase of the distance between stator blades the thermal radiation effect is diminished. Finally, by decrease of the blade distance the failure probability and creep plastic deformation decrease. Research limitations/implications – This paper describes the effect of thermal radiation in thermal-structural analysis of the gas turbine stator blade made of the super-alloy M-152. Practical implications – Blade failures in gas turbine engines often lead to loss of all downstream stages and can have a dramatic effect on the availability of the turbine engines. There are many components in a gas turbine engine, but its performance is highly profound to only a few. The majority of these are hotter end rotating components. Social implications – Three-dimensional finite element thermal and stress analyses of the blade were carried out for the steady-state full-load operation. Originality/value – In the previous works the thermal radiation effects on creep behavior of the turbine blade have not performed.
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CHEN, Otis Y., and Nobuo TAKEDA. "State-of-the-Art Materials for Future Gas Turbine Engines." Journal of the Japan Society for Aeronautical and Space Sciences 40, no. 462 (1992): 359–66. http://dx.doi.org/10.2322/jjsass1969.40.359.
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Utyashev, Farid Z., and Shamil Kh Mukhtarov. "Deformation Nanostructuring and Superplastic Processing of Metallic Materials." Materials Science Forum 838-839 (January 2016): 355–60. http://dx.doi.org/10.4028/www.scientific.net/msf.838-839.355.
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Theoretical and practical aspects of fabrication and processing of bulk metallic nanomaterials are presented. The effect of different deformation modes on the structure formation is shown. Development of nanotechnology with respect to fabrication of gas turbine engines (GTE) parts made of nanostructured superalloys is exemplified.
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Silchenko, O. B., M. V. Siluyanova, V. Е. Nizovtsev, D. A. Klimov, and A. A. Kornilov. "On the prospects of application of nanostructured heterophase polyfunctional composite materials inengine building industry." Voprosy Materialovedeniya, no. 1(93) (January 6, 2019): 50–57. http://dx.doi.org/10.22349/1994-6716-2018-93-1-50-57.
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The paper gives a brief review of properties and applications of developed extra-hard nanostructured composite materials and coatings based on them. The presentresearch suggestsaerospace applications of nanostructured composite materials based on carbides, carbonitrides and diboridesof transition and refractory metals. To improve the technical and economic performance of gas turbine engines, it is advisable to use new composite structural materials whose basic physicomechanical properties are several times superior to traditional ones. The greatest progress in developing new composites should be expected in the area of materials created on the basis of polymer, metal, intermetallic and ceramic matrices. Currently components and assemblies of gas turbine engines and multiple lighting power units with long operation life and durability will vigorously develop. Next-generation composites are studied in all developed countries, primarily in the United States and Japan.
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Sitnikov, Ilya, Dmitry Maksimov, Vladimir Batrakov, and Yury Boronnikov. "DEVELOPMENT OF A HEAT-RESISTANT THERMOBARRIER COATING FOR PARTS OF GAS TURBINE ENGINES AND GAS TURBINE PLANTS." Perm National Research Polytechnic University Aerospace Engineering Bulletin, no. 68 (2022): 5–10. http://dx.doi.org/10.15593/2224-9982/2022.68.01.
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The work is devoted to the development of new compositions of a heat-resistant thermal barrier coating for parts of gas turbine engines and gas turbine plants. The main existing materials and technologies for applying heat-resistant thermal barrier coatings are presented, and promising materials for the production of heat-resistant thermal barrier coatings are presented. The proposed new composition of the heat-resistant thermal barrier coating is a four-layer composition: as the first two heat-resistant bonding layers, materials based on nickel with the addition of aluminum, chromium, yttrium, rhenium, hafnium are used; in the last two layers, materials based on zirconium dioxide with the addition of rare earth metal oxides were used. The results of comparative tests for thermal cyclic resistance, isothermal heat resistance of samples from a superalloy based on nickel with a new composition of a heat-resistant thermal barrier coating and compositions existing at JSC "UEC-Perm Motors" are presented. And also measured the thermal diffusivity by the method of laser flash of samples from a superalloy based on nickel with a new and one of the existing at JSC «UEC-Perm Motors» compositions of the heat-resistant thermal barrier coating. The use of the developed composition of a heat-resistant thermal barrier coating makes it possible to significantly increase the service life of parts of the hot part of gas turbine engines and gas turbine plants, as well as to ensure the performance of parts on new and promising products with an increased operating temperature. Today, in conditions JSC «UEC-Perm Motors», a new composition of a heat-resistant thermal barrier coating is used in the manufacture of gas turbine plants and gas turbine engines based on PS90-A.
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Storace, A. F., D. Sood, J. P. Lyons, and M. A. Preston. "Integration of Magnetic Bearings in the Design of Advanced Gas Turbine Engines." Journal of Engineering for Gas Turbines and Power 117, no. 4 (October 1, 1995): 655–65. http://dx.doi.org/10.1115/1.2815450.
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Active magnetic bearings provide revolutionary advantages for gas turbine engine rotor support. These advantages include tremendously improved vibration and stability characteristics, reduced power loss, improved reliability, fault tolerance, and greatly extended bearing service life. The marriage of these advantages with innovative structural network design and advanced materials utilization will permit major increases in thrust-to-weight performance and structural efficiency for future gas turbine engines. However, obtaining the maximum payoff requires two key ingredients. The first is the use of modern magnetic bearing technologies such as innovative digital control techniques, high-density power electronics, high-density magnetic actuators, fault-tolerant system architecture, and electronic (sensorless) position estimation. This paper describes these technologies and the test hardware currently in place for verifying the performance of advanced magnetic actuators, power electronics, and digital controls. The second key ingredient is to go beyond the simple replacement of rolling element bearings with magnetic bearings by incorporating magnetic bearings as an integral part of the overall engine design. This is analogous to the proper approach to designing with composites, whereby the designer tailors the geometry and load-carrying function of the structural system or component for the composite instead of simply substituting composites in a design originally intended for metal material. This paper describes methodologies for the design integration of magnetic bearings in gas turbine engines.
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Jianhua, Yu, Li Xun, Zhao Wenshuo, Qin Bin, and Zhang Yu. "A brief review on the status of machining technology of fir-tree slots on aero-engine turbine disk." Advances in Mechanical Engineering 14, no. 7 (July 2022): 168781322211134. http://dx.doi.org/10.1177/16878132221113420.
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The machining precision and its consistency of turbine disk fir-tree slots have a direct influence on the performance of aero-engine rotor components. However, the structural dimensions of fir-tree slot are small, and the cutting performance of materials is extremely poor, which lead to great difficulty in machining and very few available machining methods. With the application of new materials in the aero-engines, the machining precision and quality requirements of fir-tree slots are further improved. Therefore, many research achievements on the high-efficiency, high-quality and low-cost machining technology of turbine disk fir-tree slots have been obtained. By summarizing and classifying the machining methods of aero-engine turbine disk fir-tree slots, a brief review on the characteristics of different methods are presented in detail, which provide a reference for selecting the appropriate machining method of turbine disk fir-tree slots in the field of aviation manufacturing. Meanwhile, combined with the research and application status of machining technology of turbine disk fir-tree slots, it is presented that multi-process compound machining is an effective method to realize high-efficiency, high-quality and low-cost precision machining of turbine disk fir-tree slots, such as wire electro discharge machining (wire-EDM) and profiled grinding, wire electrochemical machining (wire-ECM) and profiled grinding, wire-EDM and broaching, milling and broaching.
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Reznik, S. V., D. V. Sapronov, T. D. Karimbaev, and M. A. Mezencev. "The Determination of Rational Parameters of Lock Joints of Ceramic Blades with a Metal Disk in Advanced Aircraft Gas Turbine Engines. Part II. Testing of the Rotor Model." Proceedings of Higher Educational Institutions. Маchine Building, no. 7 (712) (July 2019): 76–84. http://dx.doi.org/10.18698/0536-1044-2019-7-76-84.
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The limited thermal stability of commonly used nickel alloys is an obstacle to further increases in operating temperatures in aircraft gas turbine engines. Alternative solutions that overcome the limitations of the operating temperatures of the gas in front of the turbine can be achieved using ceramic materials, including ceramic composites used for manufacturing blades and rotor. Due to a number of design and technological limitations associated with the production of fully ceramic parts of gas turbine engines, the option of connecting metal impellers with blades made of monolithic ceramic material deserves attention. A design of a model steel impeller with blades made of silicon carbide ceramics with reinforcing diamond particles is proposed. To determine the bearing capacity of the ‘dovetail’ type lock joint, bench tests were carried out. A computer program for probabilistic evaluation of the strength of ceramic parts is developed. A conclusion is made about the required characteristics of ceramic materials for the use in turbine impellers.
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Clemens, Helmut, and Svea Mayer. "Advanced Intermetallic TiAl Alloys." Materials Science Forum 879 (November 2016): 113–18. http://dx.doi.org/10.4028/www.scientific.net/msf.879.113.
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Challenging issues concerning energy efficiency and environmental politics require novel approaches to materials design. A recent example with regard to structural materials is the emergence of lightweight intermetallic TiAl alloys. Their excellent high-temperature mechanical properties, low density, and high stiffness constitute a profile perfectly suitable for their application as advanced aero-engine turbine blades or as turbocharger turbine wheels in next-generation automotive engines. Advanced so-called 3rd generation TiAl alloys, such as the TNM alloy described in this paper, are complex multi-phase alloys which can be processed by ingot or powder metallurgy as well as precision casting methods. Each process leads to specific microstructures which can be altered and optimized by thermo-mechanical processing and/or subsequent heat treatments.
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Uhlmann, Eckart, and Florian Heitmüller. "Improving Efficiency in Robot Assisted Belt Grinding of High Performance Materials." Advanced Materials Research 907 (April 2014): 139–49. http://dx.doi.org/10.4028/www.scientific.net/amr.907.139.
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In gas turbines and turbo jet engines, high performance materials such as nickel-based alloys are widely used for blades and vanes. In the case of repair, finishing of complex turbine blades made of high performance materials is carried out predominantly manually. The repair process is therefore quite time consuming. And the costs of presently available repair strategies, especially for integrated parts, are high, due to the individual process planning and great amount of manually performed work steps. Moreover, there are severe risks of partial damage during manually conducted repair. All that leads to the fact that economy of scale effects remain widely unused for repair tasks, although the piece number of components to be repaired is increasing significantly. In the future, a persistent automation of the repair process chain should be achieved by developing adaptive robot assisted finishing strategies. The goal of this research is to use the automation potential for repair tasks by developing a technology that enables industrial robots to re-contour turbine blades via force controlled belt grinding.
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Zeng, Yijin, Jin Wang, Shidong Ding, Haobo Zhou, Yanbin Zang, and Fangtao Li. "Simulation Study on Dynamics of Hydraulic Turbines Used in Drilling Engineering." Shock and Vibration 2020 (August 26, 2020): 1–14. http://dx.doi.org/10.1155/2020/8852874.
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Hydroturbines have a very wide range of applications, which are commonly found in wind turbines, water turbines, aero engines, etc. This paper provided a detailed turbine design and a design method of turbine blade shape. Using the CFD (computational fluid dynamics) method, based on the realizable k-ɛ turbulence model and Euler multiphase flow model, the effects of different external loads, blade numbers, blade installation angles, and flow rates on the force condition of turbine and the influence of different solid contents, particle sizes, and densities on turbine performance were studied. The simulation results show that, under the action of fluid, when the starting torque of turbine is larger than the external load, the turbine starts to move, the angular velocity increases until it remains constant, the absolute value of impact force decreases, and the impact torque decreases until it is equal to the external load; while the starting torque of turbine is smaller than the external load, the turbine stays still. The increase of the particle size, content, and density of the solid phase will lead to an increase in the torque and pressure drop of the turbine and ultimately leads to the increase of turbine input, output power, and efficiency.
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Tovkach, Serhii. "Control Laws of the Aviation Gas Turbine Engine." Electronics and Control Systems 2, no. 72 (September 23, 2022): 20–25. http://dx.doi.org/10.18372/1990-5548.72.16938.
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The article is devoted to the solution of an important scientific and applied problem of improving the dynamic characteristics of an aviation engine and ensuring flight safety and the efficiency of aircraft operation, taking into account the properties of adaptive control of an aviation gas turbine engine: <structure><functioning><adaptation><development>. Based on the concept of creating perspective aviation engines with an increased level of control automation and with units operating at elevated temperatures and protected from high-energy electromagnetic radiation, the basic laws of controlling an aviation gas turbine engine in throttle modes, low-throttle mode, gas intake and discharge modes, and start-up mode are defined. To improve the working process of the engine, it is proposed to use the gas turbine engine control system as a mechatronic system based on the principle of adaptation. With the help of the Laplace transformation, the dynamic characteristics of the power plant were determined and the mathematical model of the power plant was investigated as a constructive aspect of the automatic control system. The gas turbine and the supersonic air manifold can to some extent be considered as independent control objects, replacing the connections between them with disturbing influences. For the control and limitation circuits, it is necessary to create control programs that calculate the values of the control parameters of the turbocharger rotor speed and gas temperature behind the turbine. Regulation of fuel consumption is carried out according to the derivative of the control parameters.
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Kolomytsev, P. T., and V. M. Samoilenko. "Combined coating for turbine blades of high-temperature gas turbine engines." Metal Science and Heat Treatment 48, no. 11-12 (November 2006): 558–61. http://dx.doi.org/10.1007/s11041-006-0135-6.
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Mayer, Svea, Michael Kastenhuber, and Helmut Clemens. "Advanced Titanium Aluminides - How to Improve the Creep Resistance via Compositional and Microstructural Optimization." Materials Science Forum 941 (December 2018): 1484–89. http://dx.doi.org/10.4028/www.scientific.net/msf.941.1484.
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Intermetallic TiAl alloys based on the γ-TiAl phase are already used as engineering light-weight high-temperature materials in aircraft and automotive engines. Thereby, they partly substitute the twice as heavy Ni-base superalloys. Present applications are, for example, blades in the low-pressure turbine of advanced aero-engines, turbine wheels for turbocharger systems of car diesel engines as well as engine parts used in racing cars. All these applications require balanced mechanical properties, i.e. certain ductility at room temperature as well as defined creep strength at elevated temperatures. The first part of this paper reviews the alloy design strategy, which was used for the development of a β-solidifying γ-TiAl-based alloy, the so-called “TNM alloy”, which exhibits an excellent hot-deformability. In the meantime, the TNM alloy with the nominal composition of Ti-43.5Al-4Nb-1Mo-0.1B (in atomic percent, at.%) is introduced in a particular eco-friendly and fuel-saving aero-engine, which is powering a medium-range aircraft since the beginning of 2016. In the second part of this work the microstructural parameters are highlighted, which influence the failure strain at room temperature and creep strength at elevated temperatures. It will be shown how the creep resistance can be improved by tailoring phase fractions as well as the spatial arrangement of the microstructural constituents.
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McEntire, B. J., R. R. Hengst, W. T. Collins, A. P. Taglialavore, and R. L. Yeckley. "Ceramic Component Processing Development for Advanced Gas Turbine Engines." Journal of Engineering for Gas Turbines and Power 115, no. 1 (January 1, 1993): 1–8. http://dx.doi.org/10.1115/1.2906678.
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Norton/TRW Ceramics (NTC) is developing ceramic components as part of the DOE-sponsored Advanced Turbine Technology Applications Project (ATTAP). NTC’s work is directed at developing manufacturing technologies for rotors, stators, vane-seat platforms, and scrolls. The first three components are being produced from a HIPed Si3N4, designated NT154. Scrolls were prepared from a series of siliconized silicon-carbide (Si-SiC) materials designated NT235 and NT230. Efforts during the first three years of this five-year program are reported. Developmental work has been conducted on all aspects of the fabrication process using Taguchi experimental design techniques. Appropriate materials and processing conditions were selected for power beneficiation, densification, and heat-treatment operations. Component forming has been conducted using thermal-plastic-based injection molding (IM), pressure slip-casting (PSC), and Quick-Set™ injection molding.1 An assessment of material properties for various components from each material and process were made. For NT154, characteristic room-temperature strengths and Weibull Moduli were found to range between ≈920 MPa to ≈1 GPa and ≈10 to ≈19, respectively. Process-induced inclusions proved to be the dominant strength-limiting defect regardless of the chosen forming method. Correction of the lower observed values is being addressed through equipment changes and upgrades. For the NT230 and NT235 Si-SiC, characteristic room-temperature strengths and Weibull Moduli ranged from ≈240 to ≈420 MPa, and 8 to 10, respectively. At 1370°C, strength values for both the HIPed Si3N4 and the Si-SiC materials ranged from ≈480 MPa to ≈690 MPa. The durability of these materials as engine components is currently being evaluated.
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Nowotnik, Andrzej, Krzysztof Kubiak, Jan Sieniawski, Paweł Rokicki, Paweł Pędrak, and Grazyna Mrówka-Nowotnik. "Development of Nickel Based Superalloys for Advanced Turbine Engines." Materials Science Forum 783-786 (May 2014): 2491–96. http://dx.doi.org/10.4028/www.scientific.net/msf.783-786.2491.
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Superalloys have been developed for specific, dedicated properties and applications. One of the main application for this material is advanced, high-performance aircraft engines elements. Turbine engine creates harsh environments for materials due to the high operating temperature and stress level. Hence, as described in this article, many alloys used in the turbine section of these engines are very complex and highly optimized. This article provides an overview of structural changes that occur during the aging process of wrought and cast alloys and provides insight into the use of precipitated particles to achieve desired structures. Example will focus on alloy Inconel 718 and CMSX-4. Functional properties of these alloys can be achieved by choosing proper heat treatment parameters to obtain required rate between secondary phases. The paper also attempts to determine structural perfection and changes of crystallographic orientation along the axis of growth of single crystal nickel superalloys cast using X-ray topography and Laue diffraction method. Single crystal bars and turbine blades were manufactured in VIM furnace using the Bridgeman method. Withdrawing rates typical for CMSX-4 superalloy were used. It has been found that with increasing withdrawing rate the nature of distribution along the axis of growth of the angle of [001] direction deviation from the axis of single crystal blades growth had changed. The change of the withdrawing rate results also in the rotation of γ’ phase in the form of cubes against the axis of single crystal blades growth.
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Lacaze, Jacques, and Alain Hazotte. "Directionally Solidified Materials: Nickel-base Superalloys for Gas Turbines." Textures and Microstructures 13, no. 1 (January 1, 1990): 1–14. http://dx.doi.org/10.1155/tsm.13.1.
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From the first forged turbine blades made of iron base alloys to the present nickel base single-grain turbine blades and vanes manufactured by directional solidification, an enormous amount of research has been directed to attaining the hottest possible combustion chamber temperatures in jet engines. Temperature has been increased by about 15 K each year for the last two decades, improving the thermodynamic efficiency of the engines. The more recent developments concern the manufacturing of single-grain parts made of nickel base superalloys with large amount of the γ′ hardening phase.This paper first presents the directional solidification process used to produce single-grain parts, the formation of as-cast microstructures and the defects that can arise during solidification. In the second part the thermal treatments that are applied to the nickel base superalloys in order to enhance their mechanical properties are detailed. The effect of crystallographic orientation and of the γ/γ′ microstructure on the mechanical properties is briefly presented, as well as the. microstructural changes that can possibly arise during service.
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Simons, Emerald, and Valentin Soloiu. "Reduction of Aircraft Gas Turbine Noise with New Synthetic Fuels and Sound Insulation Materials." Transportation Research Record: Journal of the Transportation Research Board 2603, no. 1 (January 2017): 50–64. http://dx.doi.org/10.3141/2603-06.
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The need to reduce the sound and vibration characteristics in the aerospace industry is continuously increasing because of the need to meet FAA regulations, to reduce noise pollution, and to improve customer satisfaction. To improve customer satisfaction, aircraft and engine manufacturers must work to control sound and vibration levels so that passengers do not experience discomfort during a flight. Sound and vibration characteristics of a fixed-wing aircraft with jet engines are composed of complex-frequency contents that challenge engineers in the development of quiet engine designs, aerodynamic bodies, and advanced sound- and vibration-attenuating materials. One of the noisiest parts of an aircraft, the gas turbine, was analyzed in this research. In Part 1 of this project, the use of alternative fuels in a gas turbine engine was investigated to determine whether those fuels have negative effects on sound and vibration levels. Three types of fuels were used: Jet A as the reference fuel, natural gas–derived S-8, and coal-derived isoparaffinic kerosene (IPK). The alternative fuels, S-8 and IPK, are Fischer–Tropsch process fuels. Overall sound and vibration characteristics of the alternative fuels presented a similar pattern across the frequency spectrum to those of the reference fuel, with the alternative fuels being slightly quieter. In Part 2, the sound path was treated by introducing sound-absorbing materials and investigating their acoustic performance. A melamine-based foam and soy-based foam were used in this research. Melamine is very lightweight, has excellent thermal endurance, and is hydrophobic. The soy-based foam was selected for its potential application in the aerospace industry to work toward a greener aircraft, in an effort to promote environmental sustainability. The soy-based material reduced the sound level by more than 20 dB(A) and presented better performance than the melamine at high frequencies.