Gotowe bibliografie tematyczne / Turbine engines materials

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Gotowa bibliografia na temat „Turbine engines materials”

Autor: Grafiati

Data publikacji: 6 września 2023

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Artykuły w czasopismach na temat "Turbine engines materials"

Pyatov, I. S., O. V. Shiboev, V. G. Buzinov, A. R. Makarov, A. V. Kostyukov, V. N. Posedko, L. A. Finkelberg i A. N. Kostyuchenkov. "Carbon materials for parts of gas-turbine engines and internal combustion engines, problems and prospects". Izvestiya MGTU MAMI 8, nr 4-1 (20.02.2014): 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, nr 1 (1.01.1989): 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, nr 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 (marzec 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 i Jingbo Luo. "Angle-Regulating Rule of Guide Vanes of Variable Geometry Turbine Adjusting Mechanism". Applied Sciences 13, nr 11 (23.05.2023): 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, nr 4 (1.11.2006): 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, nr 4 (lipiec 1988): 213–19. http://dx.doi.org/10.1016/0261-3069(88)90033-7.

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Easley, M. L., i J. R. Smyth. "Ceramic Gas Turbine Technology Development". Journal of Engineering for Gas Turbines and Power 117, nr 4 (1.10.1995): 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, i Przemysław Golewski. "The Analysis of Heat Transfer and Thermal Stresses in Thermal Barrier Coatings under Exploitation". Defect and Diffusion Forum 326-328 (kwiecień 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, i Shiladitya Paul. "Progress in Novel Electrodeposited Bond Coats for Thermal Barrier Coating Systems". Materials 14, nr 15 (28.07.2021): 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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Rozprawy doktorskie na temat "Turbine engines materials"

Temple, Benjamin John. "Advancements of Gas Turbine Engines and Materials". OpenSIUC, 2020. https://opensiuc.lib.siu.edu/theses/2763.

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This thesis starts out with a brief description of gas turbine engines and information on railroad locomotives being the gas-turbine electric locomotives with some comparison of the diesel-electric locomotives in the introduction. Section 1.1 is the research problem looking at the older gas turbine electric locomotives in the 1950’s that ran on the rail and the problems they suffered. In section 1.2 titled the purpose of the study takes a look at newer gas turbine locomotives that were being consider or has been built with improvements since the 1950’s. The objective of the study being section 1.3 looks at the advantages of new gas turbines engines. Section 1.4 titled the research questions discusses better materials and methods of gas turbine engines. Chapter 2 is the literature review looking at the fuel oil specifications being number 4, number 5, and number 6. This chapter also talks about the used of distillates, types of distillates, composition of distillates, specifications for distillates, residual fuel oil and fuel oil quality dealing with the firing of gas turbine engines. Section 2.3 of chapter 2 being titled power generation looks at power plant gas-turbine engines and the power they produce. Chapter 3, titled the proposed methodology looks at setting up an experiment using a gas-turbine engine and a diesel-electric engine to compare the advantages of along with the disadvantages. Section 3.1 is titled data collected, within this section is discussion on the data collected from the experiment and improvements that could be made to the gas turbine engines. The end of chapter 3, section 3.2 titled data analyzing, talks about possible the results collected, calculations done, improvements made and rerunning another experiment with the improvements made. Chapter 4 discuss the types of materials using in building the compressor and turbine blades. Last, but not least is chapter 5 which discusses the actual experiment using the gas turbine simulator for aircrafts and how to apply it to the railroad locomotives. After the conclusion which discusses the results, is the appendix a being gas tables, appendix b being trial run 1 and appendix c being trial run 2.

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Cornwell, Michael. "Causes of Combustion Instabilities with Passive and Active Methods of Control for practical application to Gas Turbine Engines". University of Cincinnati / OhioLINK, 2011. http://rave.ohiolink.edu/etdc/view?acc_num=ucin1307323433.

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Roth, Richard. "Materials substitution in aircraft gas turbine engine applications". Thesis, Massachusetts Institute of Technology, 1992. http://hdl.handle.net/1721.1/13112.

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Saari, Henry M. J. "The processing of gas turbine engine hot section materials through directional solidification". Thesis, National Library of Canada = Bibliothèque nationale du Canada, 2000. http://www.collectionscanada.ca/obj/s4/f2/dsk1/tape4/PQDD_0018/MQ48472.pdf.

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Saari, Henry M. J. Carleton University Dissertation Engineering Mechanical and Aerospace. "The Processing of gas turbine engine hot section materials through directional solidification". Ottawa, 1999.

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Everitt, Stewart. "Developments in advanced high temperature disc and blade materials for aero-engine gas turbine applications". Thesis, University of Southampton, 2012. https://eprints.soton.ac.uk/348897/.

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The research carried out as part of this EngD is aimed at understanding the high temperature materials used in modern gas turbine applications and providing QinetiQ with the information required to assess component performance in new propulsion systems. Performance gains are achieved through increased turbine gas temperatures which lead to hotter turbine disc rims and blades. The work has focussed on two key areas: (1) Disc Alloy Assessment of High Temperature Properties; and (2) Thermal Barrier Coating Life Assessment; which are drawn together by the overarching theme of the EngD: Lifing of Critical Components in Gas Turbine Engines. Performance of sub-solvus heat treated N18 alloy in the temperature range of 650°C to 725°C has been examined via monotonic and cyclically stabilised tensile, creep and strain controlled low cycle fatigue (LCF) tests including LCF behaviour in the presence of a stress concentration under load-control. Crack propagation studies have been undertaken on N18 and a particular super-solvus heat treatment variant of the alloy LSHR at the same temperatures, in air and vacuum with 1s and 20s dwell times. Comparisons between the results of this testing and microstructural characterisation with RR1000, UDIMET® 720 Low Interstitial (U720Li) and a large grain variant of U720Li have been carried out. In all alloys, strength is linked to a combination of γ' content and grain size as well as slow diffusing atoms in solid solution. High temperature strength improves creep performance which is also dependent on grain size and grain boundary character. Fatigue testing revealed that N18 had the most transgranular crack propagation with a good resistance to intergranular failure modes, with U720Li the most intergranular. Under vacuum conditions transgranular failure modes are evident to higher temperature and ΔK, with LSHR failing almost completely by intergranular crack propagation in air. For N18 significant cyclic softening occurs at 725°C with LCF initiation occurring at pores and oxidised particles. An apparent activation energy technique was used to provide further insights into the failure modes of these alloys, this indicating that, for N18 with 1s dwell, changes in fatigue crack growth rates were attributed to static properties and for LSHR, with 20s dwell in air, that changes were attributed to the detrimental synergistic combination of creep and oxidation at 725°C. Microchemistry at grain boundaries, especially M23C6 carbides, plays an important role in these alloys. Failure mechanisms within a thermal barrier coating (TBC) system consisting of a CMSX4 substrate, PtAl bond coat, thermally grown oxide (TGO) layer and a top coat applied using electron beam physical vapour deposition have been considered. TGO growth has been quantified under isothermal, two stage temperature and thermal cyclic exposures. An Arrhenius relation was used to describe the TGO growth and produce an isothermal TGO growth model. The output from this was used in the QinetiQ TBC Lifing Model. Thermo-mechanical fatigue test methods were also developed including a novel thermocouple placement permitting substrate temperature to be monitored without disturbing the top coat such that the QinetiQ TBC Lifing Model could be validated. The importance of material, system specific knowledge and performance data with respect to a particular design space for critical components in gas turbine engines has been highlighted. Data and knowledge regarding N18, LSHR and TBC systems has been added to the QinetiQ’s databank enhancing their capability for providing independent advice regarding high temperature materials particularly in new gas turbine engines.

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Ghulam, Mohamad. "Characterization of Swirling Flow in a Gas Turbine Fuel Injector". University of Cincinnati / OhioLINK, 2019. http://rave.ohiolink.edu/etdc/view?acc_num=ucin1563877023803877.

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Dsouza, Jason Brian. "Numerical Analysis of a Flameless Swirl Stabilized Cavity Combustor for Gas Turbine Engine Applications". University of Cincinnati / OhioLINK, 2021. http://rave.ohiolink.edu/etdc/view?acc_num=ucin1627663015527799.

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Sahay, Prateek. "Development of a Robotic Cell for Removal of Tabs from Jet Engine Turbine Blade". University of Cincinnati / OhioLINK, 2019. http://rave.ohiolink.edu/etdc/view?acc_num=ucin1574417686354007.

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Aull, Mark J. "Comparison of Fault Detection Strategies on a Low Bypass Turbofan Engine Model". University of Cincinnati / OhioLINK, 2011. http://rave.ohiolink.edu/etdc/view?acc_num=ucin1321368833.

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Książki na temat "Turbine engines materials"

E, Helms Harold, red. Ceramic applications in turbine engines. Park Ridge, N.J., U.S.A: Noyes Publications, 1986.

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The Impact of advanced materials on small turbine engines. [Warrendale, Pa: Society of Automotive Engineers, 1991.

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P, Millan P., i United States. National Aeronautics and Space Administration., red. Oxide-dispersion-strengthened turbine blades: Materials for advanced turbine engines, project completion report, project 4. [Phoenix, Ariz.]: Garrett Turbine Engine Co., 1987.

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Wallace, William. Methods for crack growth testing in gas turbine engine disc materials. Ottawa: National Aeronautical Establishment, 1987.

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Miller, Robert A. Thermal barrier coatings for gas turbine and diesel engines. [Washington, D.C.]: NASA, 1990.

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J, Brindley W., Bailey M. Murray i United States. National Aeronautics and Space Administration., red. Thermal barrier coatings for gas turbine and diesel engines. [Washington, D.C.]: NASA, 1990.

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Melvin, Freling, Friedrich L. A i Lewis Research Center, red. Materials for Advanced Turbine Engines (MATE): Project 4--erosion resistant compressor airfoil coating. [Cleveland, Ohio]: National Aeronautics and Space Administration, 1987.

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M, Baldwin Richard, Schick Wilbur R, United States. National Aeronautics and Space Administration. i United States. Army Aviation Systems Command., red. Spray automated balancing of rotors: Methods and materials. [Washington, D.C.]: National Aeronautics and Space Administration, 1988.

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Center, Lewis Research, i United States. National Aeronautics and Space Administration. Scientific and Technical Information Branch, red. Turbine engine hot section technology 1986: Proceedings of a conference. [Washington, D.C.]: National Aeronautics and Space Administration, Scientific and Technical Information Branch, 1986.

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Części książek na temat "Turbine engines materials"

Navrotsky, V., Y. Nozhnitsky, Y. Shekhtman, N. Boutourlinova, Y. Fedina i E. Chyiaston. "Designing Gas Turbine Ceramic Elements". W 4th International Symposium on Ceramic Materials and Components for Engines, 1035–41. Dordrecht: Springer Netherlands, 1992. http://dx.doi.org/10.1007/978-94-011-2882-7_115.

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Butler, E. G., i M. H. Lewis. "Prospects for Ceramics in Airborne Gas Turbine Engines". W 4th International Symposium on Ceramic Materials and Components for Engines, 32–49. Dordrecht: Springer Netherlands, 1992. http://dx.doi.org/10.1007/978-94-011-2882-7_3.

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Watanabe, Keiichiro, Tadao Ozawa, Yoshito Kobayashi i Eito Matsuo. "Development of Silicon Nitride Radial Turbine Rotors". W 4th International Symposium on Ceramic Materials and Components for Engines, 1009–16. Dordrecht: Springer Netherlands, 1992. http://dx.doi.org/10.1007/978-94-011-2882-7_112.

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Nozhnitsky, Y., L. Smirnov, S. Egorov, A. Markov i V. Sakovich. "Experimental Investigation of Ceramic Materials and Turbine Rotor Components Strength". W 4th International Symposium on Ceramic Materials and Components for Engines, 1025–34. Dordrecht: Springer Netherlands, 1992. http://dx.doi.org/10.1007/978-94-011-2882-7_114.

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Russ, Stephan M., Reji John i Craig P. Przybyla. "Characterization and Simulation of Time-Dependent Response of Structural Materials for Aero Structures and Turbine Engines". W Challenges in Mechanics of Time Dependent Materials, Volume 2, 83–91. Cham: Springer International Publishing, 2017. http://dx.doi.org/10.1007/978-3-319-63393-0_14.

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Gostic, William. "Application of Materials and Process Modeling to the Design, Development, and Sustainment of Advanced Turbine Engines". W Superalloys 2012, 1–12. Hoboken, NJ, USA: John Wiley & Sons, Inc., 2012. http://dx.doi.org/10.1002/9781118516430.ch1.

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Bunker, Ron S. "The Role of Materials and Manufacturing Technologies as Enablers in Gas Turbine Cooling for High Performance Engines". W Ceramic Transactions Series, 1–20. Hoboken, NJ, USA: John Wiley & Sons, Inc., 2009. http://dx.doi.org/10.1002/9780470528976.ch1.

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Shmotin, Yuriy, Alexander Logunov, Denis Danilov i Igor Leshchenko. "Development of Economically Doped Heat-Resistant Nickel Single-Crystal Superalloys for Blades of Perspective Gas Turbine Engines". W Proceedings of the 8th Pacific Rim International Congress on Advanced Materials and Processing, 327–36. Cham: Springer International Publishing, 2013. http://dx.doi.org/10.1007/978-3-319-48764-9_40.

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Straub, Douglas L., i Geo A. Richards. "Effects of Alternative Fuels and Engine Cycles on Turbine Cooling". W Turbine Aerodynamics, Heat Transfer, Materials, and Mechanics, 655–73. Reston, VA: American Institute of Aeronautics and Astronautics, Inc., 2014. http://dx.doi.org/10.2514/5.9781624102660.0655.0674.

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Hessler, U., i B. Domes. "LCF-Failure Analysis of an Aero-Engine Turbine Wheel". W Low Cycle Fatigue and Elasto-Plastic Behaviour of Materials—3, 664–70. Dordrecht: Springer Netherlands, 1992. http://dx.doi.org/10.1007/978-94-011-2860-5_107.

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Streszczenia konferencji na temat "Turbine engines materials"

GRAY, DAVID. "Materials technology for small gas turbine engines". W 23rd Joint Propulsion Conference. Reston, Virigina: American Institute of Aeronautics and Astronautics, 1987. http://dx.doi.org/10.2514/6.1987-2144.

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Littles, Jerrol W., Robert J. Morris, Richard Pettit, David M. Harmon, Michael F. Savage i Sharayu Tulpule. "Materials and Structures Prognosis for Gas Turbine Engines". W ASME Turbo Expo 2006: Power for Land, Sea, and Air. ASMEDC, 2006. http://dx.doi.org/10.1115/gt2006-91203.

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Gas turbine engine diagnostic systems often utilize data trending and anomaly detection to provide a measure of system health. These systems provide significant benefits for trending shifts in engine performance and diagnosing system degradation that requires some maintenance action. However, this approach may be limited in the ability to uniquely identify damage for select components and failure modes. Advanced prognostic systems are being developed to work symbiotically with state of the art diagnostic techniques in use today; these advanced systems use advanced material and component damage evolution modelling linked with system-level structural analyses to intelligently guide the health management system to search for specific signatures that would be expected from key changes in component and system health [1,2,3,4]. Material damage models, advanced component models, and novel system-level structural analyses are being used to generate newly defined “structural transfer functions” (STFs) that provide a link between sensed parameters and the remaining capability of specific components, and the system. The characteristic damage signatures vary by component type and failure mode, and hence the specific STF approach varies among component types. An initial STF approach was developed and demonstrated for a specific component and damage type [5] under an initial feasibility program. This STF-based prognosis approach is fundamentally different from the traditional modal analysis based NDE approach used for crack detection. This presentation will review this novel STF-based prognosis approach, and consider examples of STFs characteristic of specific components and damage types, as well as progress towards the development of tools that are enabling system-level STF development [6].

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Kool, G. A. "Current and Future Materials in Advanced Gas Turbine Engines". W ASME 1994 International Gas Turbine and Aeroengine Congress and Exposition. American Society of Mechanical Engineers, 1994. http://dx.doi.org/10.1115/94-gt-475.

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Gas turbine engines are constructed of components with excellent strength and stiffness, a minimum density, a high temperature capability for long times, and at affordable cost. Metallic materials are the centrepiece in fulfilling these requirements. Future gas turbine engines will have to have higher thrust-to-weight ratios, better fuel efficiencies and still lower costs. This will require new and advanced lightweight materials with higher temperature capabilities. This paper discusses some of the presently applied materials in the fan, compressor and turbine sections of gas turbines, and reviews the material developments that are occurring and will be necessary for the near and long term futures.

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Mason, John L. "The Impact of Advanced Materials on Small Turbine Engines". W SAE Aerospace Atlantic Conference and Exposition. 400 Commonwealth Drive, Warrendale, PA, United States: SAE International, 1991. http://dx.doi.org/10.4271/911207.

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JOHNSON, A., i P. WRIGHT. "Application of advanced materials to aircraft gas turbine engines". W 26th Joint Propulsion Conference. Reston, Virigina: American Institute of Aeronautics and Astronautics, 1990. http://dx.doi.org/10.2514/6.1990-2281.

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Murugan, Muthuvel, Anindya Ghoshal, Fei Xu, Ming-Chen Hsu, Yuri Bazilevs, Luis Bravo i Kevin Kerner. "Articulating Turbine Rotor Blade Concept for Improved Off-Design Performance of Gas Turbine Engines". W ASME 2016 Conference on Smart Materials, Adaptive Structures and Intelligent Systems. American Society of Mechanical Engineers, 2016. http://dx.doi.org/10.1115/smasis2016-9045.

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Gas turbine engines are generally optimized to operate at nearly a fixed speed with fixed blade geometries for the design operating condition. When the operating condition of the engine changes, the flow incidence angles may not be optimum with the blade geometry resulting in reduced off-design performance. Articulating the pitch angle of turbine blades in coordination with adjustable nozzle vanes can improve performance by maintaining flow incidence angles within the optimum range at all operating conditions of a gas turbine engine. Maintaining flow incidence angles within the optimum range can prevent the likelihood of flow separation in the blade passage and also reduce the thermal stresses developed due to aerothermal loads for variable speed gas turbine engine applications. U.S. Army Research Laboratory has partnered with University of California San Diego and Iowa State University Collaborators to conduct high fidelity stator-rotor interaction analysis for evaluating the aerodynamic efficiency benefits of articulating turbine blade concept. The flow patterns are compared between the baseline fixed geometry blades and articulating conceptual blades. The computational fluid dynamics studies were performed using a stabilized finite element method developed by the Iowa State University and University of California San Diego researchers. The results from the simulations together with viable smart material based technologies for turbine blade actuations are presented in this paper.

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Shifler, David, Donald Hoffman, John Hartranft, Carl Grala, Louis Aprigliano i Dan Groghan. "USN Marine Gas Turbine Development Initiatives: Part I—Advanced High Temperature Materials". W ASME Turbo Expo 2010: Power for Land, Sea, and Air. ASMEDC, 2010. http://dx.doi.org/10.1115/gt2010-23596.

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In the 1950’s and 1960’s, the United States Navy (USN) embarked on an ambitious program to convert surface combatants from steam to gas turbine power. Navy unique engines were developed and commercial industrial engines were modified to meet the strenuous environments encountered by surface Navy ships. Ultimately, the best engines were found to be those developed from the aero-industry. However, those aero-derivative engines lacked shock hardness, vibration treatment and most importantly, they lacked the ability to survive long hours of operation in a heavy salt environment burning diesel and other poorer fuels. Those poorer fuels contained higher levels of sulfur and other chemical compounds that created a challenging environment for the aircraft engines. The aircraft engines were designed to burn much cleaner fuel with virtually no sea salt. As a result, early applications of those engines to Navy ships were disappointing. However, through aggressive materials development programs and extended endurance tests in a marine-like environment, engines including the Pratt and Whitney FT-4A and the General Electric LM2500 demonstrated themselves to be superior replacements for traditional Navy steam propulsion plants. The LM2500 eventually became the workhorse of the USN surface fleet and has proven to be an excellent engine. Nevertheless, as fuels become more costly and quality sometimes questionable, the Navy is interested in another leap forward. This leap is anticipated to again be based on aero-derivative engines, but will be focused on smaller, lighter, and more fuel efficient engines that will have the capability of burning the alternative fuels of the future. The Office of Naval Research (ONR) is contemplating a comprehensive program of materials developments, Phase I, which will facilitate the marinization of the highly efficient gas turbine engines being developed in various Air Force and commercial engine development programs. Marinization issues could include improving the performance of ceramic matrix composites in a marine environment and minimizing the affects of higher temperatures on disc corrosion in the final stages of the compressor and in the hot-section. A Phase II program is also contemplated that will then develop a series of engines for various future USN applications based on the results of the Phase I Program. This paper will describe the programs that are being contemplated.

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Birdsall, James C., William J. Davies, Richard Dixon, Matthew J. Ivary i Gary A. Wigell. "Potential Application of Composite Materials to Future Gas Turbine Engines". W 1988 American Control Conference. IEEE, 1988. http://dx.doi.org/10.23919/acc.1988.4790028.

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Murugan, Muthuvel, Anindya Ghoshal, Michael Walock i Daniel Bonis. "Intelligent Propulsion Materials for Rotorcraft Gas Turbine Engine Component Applications". W Vertical Flight Society 75th Annual Forum & Technology Display. The Vertical Flight Society, 2019. http://dx.doi.org/10.4050/f-0075-2019-14683.

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Rotorcraft gas turbine engines are subject to sand particle ingestion problems during take-off, landing, and hovering operations in sandy desert regions. Although most of the rotorcraft gas turbine engines are fitted with inertial particle separators, they are not efficient in filtering out fine sand particles of size of 75 microns or below. Inlet barrier filters may be efficient in filtering fine particles in the intake air-flow, but they cause engine power loss penalty due to significantly high inlet pressure losses. The sand particles in the air-flow cause severe erosion damage on compressor blades, and molten sand glazing coupled with Calcia-Magnesia-Alumino-Silicates (CMAS) attack on hot-section turbine blades. Due to particle impacts and CMAS attack, the coatings on the blades wear out, form cracks and delaminate over time causing huge maintenance burden for rotorcraft gas turbine engines operating in sandy regions. The objective of this research is to discover a revolutionary, in-situ sensing material system that is capable of monitoring the health of propulsion component materials using co-doped luminescent materials in the erosion resistant coatings or thermal barrier coatings (TBCs) of engine components. This paper presents the research efforts and results from the CCDC - Army Research Laboratory, Vehicle Technology Directorate Director's seedling initiative project that investigated the effectiveness of triboluminescent materials interspersed with blade coatings in a layered form for detecting cracks/fractures that may occur in blade coatings due to sand particle exposure under engine relevant conditions. Use of appropriate instrumentations for in-situ luminescence detection methods to identify cracks/fractures in coatings is also discussed.

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Battison, J. Mark. "Mechanical Attachment of Ceramics to Metals in Gas Turbine Engines". W ASME 1993 International Gas Turbine and Aeroengine Congress and Exposition. American Society of Mechanical Engineers, 1993. http://dx.doi.org/10.1115/93-gt-434.

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Williams International has been actively investigating the use of ceramic materials in gas turbine engines for over 10 years. Ceramic component applications include both static and dynamic components such as combustors and turbine rotors. Component stresses, material properties, and cost, dictate attachment strategies. Non-metallic turbines with metal-to-non-metallic attachment schemes have been successfully demonstrated. This paper reviews a progression of attachment strategies that eventually led to a successful test of a non-metallic turbine in a gas turbine engine.

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Raporty organizacyjne na temat "Turbine engines materials"

Arsenlis, Athanasios, i John Allison. Integrated Computational Materials Engineering (ICME) Tools for Optimizing Strength of Forged Al-Li Turbine Blades for Aircraft Engines Final Report CRADA No. TC02238.0. Office of Scientific and Technical Information (OSTI), wrzesień 2017. http://dx.doi.org/10.2172/1425447.

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Arsenlis, A., i J. Allison. Integrated Computational Materials Engineering (ICME) Tools for Optimizing Strength of Forged Al-Li Turbine Blades for Aircraft Engines Final Report CRADA No. TC02238.0. Office of Scientific and Technical Information (OSTI), marzec 2021. http://dx.doi.org/10.2172/1774219.

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Taylor. L51755 Development and Testing of an Advanced Technology Vibration Transmission. Chantilly, Virginia: Pipeline Research Council International, Inc. (PRCI), lipiec 1996. http://dx.doi.org/10.55274/r0010124.

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Fiber optic sensors have been under development in industrial and government laboratories around the world for over a decade. The commercial market for fiber sensors for measuring parameters such as temperature, displacement, and liquid level is now estimated to exceed $100 M/year. Aside from the commercial interest, the U. S. Department of Defense has vigorously pursued the development of fiber gyroscopes and hydrophones. In spite of the high level of research and development activity, however, until recently fiber sensors had not been successfully applied in high-temperature engine environments. The goal of this effort is to develop and test high-temperature fiber optic sensors and show that they are suitable for monitoring vibration and other instabilities in gas turbine engines. The underlying technology developed during the course of PRCI projects PR- 219-9120 and PR-219-9225 during 1991-94 serves as the foundation for PR-240-9416. Transducers with the fiber optic Fabry-Perot interferometer (FFPI) configuration have been adapted for use in the turbomachinery environment.To ensure the survival of the FFPI sensors at high temperatures, two techniques for coating the fibers with metal have been developed: electroplating and vacuum deposition. Coated sensors have subsequently been embedded in aluminum and brass alloys. Experiments on a small Sargent Welch turbine engine have shown the high sensitivity of embedded FFPI strain sensors to vibration in rolling bearings. Data have been collected in both the time and frequency domain. A new accelerometer design in which a metal-coated fiber containing the FFPI element is soldered directly to a diaphragm in a stainless steel housing shows response similar to a piezoelectric accelerometer in shaker table tests. The high sensitivity of the FFPI accelerometer has been demonstrated in field tests in a Solar Centaur turbine engine, and the design has survived temperatures greater than 500�C in a test oven. A magnetometer with a physical configuration similar to that of the accelerometer has been used to measure the distance from the sensor head to a rotating shaft made of ferromagnetic material. This device, which functions as a proximity probe, has been used to monitor shaft rotation rate (keyphasor application) and as a shaft thrust position sensor. These results indicate the potential for performing critical measurements in turbine engines with FFPI sensors. They can measure acceleration, distance (proximity), strain (as it relates to bearing defect diagnosis), and gas pressure, and can operate at higher temperatures than conventional transducers.

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Fortener, William G., i Susan S. Saliba. Nonmetals Test and Evaluation. Delivery Order 0003: Fuel System Materials Compatibility Testing of Fuel Additives for Reducing the Amount of Small Particulate in Turbine Engine Exhaust. Fort Belvoir, VA: Defense Technical Information Center, październik 2005. http://dx.doi.org/10.21236/ada448662.

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