Relevant bibliographies by topics / Ceramic gas barrier coatings

Contents

  1. Journal articles
  2. Dissertations / Theses
  3. Books
  4. Book chapters
  5. Conference papers
  6. Reports

Academic literature on the topic 'Ceramic gas barrier coatings'

Author: Grafiati
Published: 4 June 2021
Last updated: 15 February 2022

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Journal articles on the topic "Ceramic gas barrier coatings"

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Wu, Shuo, Yuantao Zhao, Wenge Li, Weilai Liu, Yanpeng Wu, and Fukang Liu. "Research Progresses on Ceramic Materials of Thermal Barrier Coatings on Gas Turbine." Coatings 11, no. 1 (2021): 79. http://dx.doi.org/10.3390/coatings11010079.

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Thermal barrier coatings (TBCs) play a vitally important role in protecting the hot parts of a gas turbine from high temperature and corrosion effectively. More and more attention has been paid to the performance modification of ZrO2-based ceramics and seeking for new ceramic materials to meet requirements of gas turbine TBCs. The working principle, merits, and demerits of main technologies for coating preparation are elaborated in this paper, and the properties of new ceramic materials are reviewed. It is found that the thermal conductivity, thermal stability, mechanical properties, and other
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Wu, Shuo, Yuantao Zhao, Wenge Li, Weilai Liu, Yanpeng Wu, and Fukang Liu. "Research Progresses on Ceramic Materials of Thermal Barrier Coatings on Gas Turbine." Coatings 11, no. 1 (2021): 79. http://dx.doi.org/10.3390/coatings11010079.

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Thermal barrier coatings (TBCs) play a vitally important role in protecting the hot parts of a gas turbine from high temperature and corrosion effectively. More and more attention has been paid to the performance modification of ZrO2-based ceramics and seeking for new ceramic materials to meet requirements of gas turbine TBCs. The working principle, merits, and demerits of main technologies for coating preparation are elaborated in this paper, and the properties of new ceramic materials are reviewed. It is found that the thermal conductivity, thermal stability, mechanical properties, and other
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Wright, I. G., and B. A. Pint. "Bond coating issues in thermal barrier coatings for industrial gas turbines." Proceedings of the Institution of Mechanical Engineers, Part A: Journal of Power and Energy 219, no. 2 (2005): 101–7. http://dx.doi.org/10.1243/095765005x6836.

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Thermal barrier coatings are intended to work in conjunction with internal cooling schemes to reduce the metal temperature of critical hot gas path components in gas turbine engines. The thermal resistance is typically provided by a 100-250 μm thick layer of ceramic (most usually zirconia stabilized with an addition of 7–8 wt% of yttria), and this is deposited on to an approximately 50 μ thick, metallic bond coating that is intended to anchor the ceramic to the metallic surface, to provide some degree of mechanical compliance, and to act as a reservoir of protective scale-forming elements (Al)
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Meier, S. M., and D. K. Gupta. "The Evolution of Thermal Barrier Coatings in Gas Turbine Engine Applications." Journal of Engineering for Gas Turbines and Power 116, no. 1 (1994): 250–57. http://dx.doi.org/10.1115/1.2906801.

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Thermal barrier coatings (TBCs) have been used for almost three decades to extend the life of combustors and augmentors and, more recently, stationary turbine components. Plasma-sprayed yttria-stabilized zirconia TBC currently is bill-of-material on many commercial jet engine parts. A more durable electron beam-physical vapor deposited (EB-PVD) ceramic coating recently has been developed for more demanding rotating as well as stationary turbine components. This ceramic EB-PVD is bill-of-material on turbine blades and vanes in current high thrust engine models and is being considered for newer
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Mifune, Noriyuki, and Yoshio Harada. "2CaO･SiO2-CaO･ZrO2 Thermal Barrier Coating Formed by Plasma Spray Process." Materials Science Forum 522-523 (August 2006): 239–46. http://dx.doi.org/10.4028/www.scientific.net/msf.522-523.239.

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The applicability of 2CaO·SiO2-CaO·ZrO2 ceramic coatings as thermal barrier coatings (TBCs) was investigated. Coatings consisting of various ratios of 2CaO·SiO2-CaO·ZrO2 bond-coated with NiCrAlY were prepared using the plasma spray process. The structure of the coatings was characterized by scanning electron microscopy and X-ray diffraction analysis. The resistance of the coatings to thermal shock was evaluated with acoustic emission techniques under a thermal cycle from 1273 K to room temperature, and the hot corrosion resistance of the coatings was investigated with V2O5 and Na2SO4 at 1273 K
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Zhu, Dongming, and Robert A. Miller. "Thermal-Barrier Coatings for Advanced Gas-Turbine Engines." MRS Bulletin 25, no. 7 (2000): 43–47. http://dx.doi.org/10.1557/mrs2000.123.

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Ceramic thermal-barrier coatings (TBCs) have received increasing attention for gasturbine engine applications. The advantages of using TBCs include increased fuel efficiency by allowing higher gas temperatures and improved durability and reliability from lower component temperatures. As illustrated in Figure 1, TBCs can provide effective heat insulation to engine components, thus allowing higher operating temperatures and reduced cooling requirements. Atypical two-layer TBC system consists of a porous ZrO2-Y2O3 ceramic top coat and an oxidation-resistant metallic bond coat. These TBC systems c
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Vaßen, Robert, Holger Kassner, Alexandra Stuke, Daniel Emil Mack, Maria Ophelia D. Jarligo, and Detlev Stöver. "Functionally Graded Thermal Barrier Coatings with Improved Reflectivity and High-Temperature Capability." Materials Science Forum 631-632 (October 2009): 73–78. http://dx.doi.org/10.4028/www.scientific.net/msf.631-632.73.

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Conventional thermal barrier coating (TBC) systems consist of a duplex structure with a metallic bondcoat and a ceramic, heat isolative topcoat. In modern TBCs the ceramic topcoat is further divided into layers with different functions. One example is the double layer system in which conventional yttria stabilized zirconia (YSZ) is used as bottom and new materials as pyrochlores or perovskites are used as topcoat layers. These systems demonstrated an improved temperature capability compared to standard YSZ. Examples of such systems will be shown. In modern gas turbines the increased temperatur
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Zhong, Jie, Dongling Yang, Shuangquan Guo, Xiaofeng Zhang, Xinghua Liang, and Xi Wu. "Rear Earth Oxide Multilayer Deposited by Plasma Spray-Physical Vapor Deposition for Envisaged Application as Thermal/Environmental Barrier Coating." Coatings 11, no. 8 (2021): 889. http://dx.doi.org/10.3390/coatings11080889.

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SiC fiber-reinforced SiC ceramic matrix composites (SiCf/SiC CMCs) are being increasingly used in the hot sections of gas turbines because of their light weight and mechanical properties at high temperatures. The objective of this investigation was the development of a thermal/environmental barrier coating (T/EBC) composite coating system consisting of an environmental barrier coating (EBC) to protect the ceramic matrix composites from chemical attack and a thermal barrier coating (TBC) that insulates and reduces the ceramic matrix composites substrate temperature for increased lifetime. In th
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Stott, F. H., D. J. de Wet, and R. Taylor. "Degradation of Thermal-Barrier Coatings at Very High Temperatures." MRS Bulletin 19, no. 10 (1994): 46–49. http://dx.doi.org/10.1557/s0883769400048223.

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Thermal-barrier coatings are finding increasing use in engineering applications, particularly in gas turbines. Such coatings, consisting of ceramic insulating layers bonded to the superalloy substrate by oxidation-resistant alloy coatings, are deposited onto components to reduce heat flow through the cooled substrate and to limit operating temperature. They have been used effectively on static components such as combustor cans, flare heads, hot gas seal segments, fuel evaporators, and deflector plates, giving considerable improvements in component life. They have been used successfully on vane
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Meier, Susan Manning, Dinesh K. Gupta, and Keith D. Sheffler. "Ceramic thermal barrier coatings for commercial gas turbine engines." JOM 43, no. 3 (1991): 50–53. http://dx.doi.org/10.1007/bf03220164.

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Dissertations / Theses on the topic "Ceramic gas barrier coatings"

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Greenwood, Oliver Davey. "Non-isothermal plasma treatment of organic and inorganic polymers." Thesis, Durham University, 1997. http://etheses.dur.ac.uk/5065/.

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Increased understanding of plasma-polymer interactions is required to further the technological use of such processes, and elucidates heterogeneous physico-chemical reactions which occur under bombardment by complex combinations of energetic species. This thesis presents a systematic investigation into the effect of exposing organic and inorganic polymeric surfaces to controlled non-isothermal plasmas. Concurrently, a novel process is presented by which metal oxide gas barrier coatings are synthesized on polymer substrates by non- isothermal plasma treatment. Organic polymers exhibiting a rang
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Paul, Shiladitya. "Pore architecture in ceramic thermal barrier coatings." Thesis, University of Cambridge, 2008. http://ethos.bl.uk/OrderDetails.do?uin=uk.bl.ethos.611885.

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Fox, A. C. "Gas permeation through plasma sprayed ceramic coatings." Thesis, University of Cambridge, 1999. http://ethos.bl.uk/OrderDetails.do?uin=uk.bl.ethos.599155.

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This work has addressed the gas transport rate and mechanism through plasma sprayed coatings. This is of particular interest for thermal barrier coatings (TBCs) and solid oxide fuel cell electrodes. Deposits of ZrO<SUB>2</SUB> - 8 wt% Y<SUB>2</SUB>O<SUB>3</SUB>, ZrO<SUB>2</SUB> - 14 wt% Y<SUB>2</SUB>O<SUB>3</SUB> and A1<SUB>2</SUB>O<SUB>3</SUB> have been plasma sprayed under varying conditions. Microstructural studies and density measurements have been carried out to characterise the porosity content and microcrack distribution. Crystallographic phase analysis and Young's Modulus measurements
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Torrey, Jessica D. "Polymer derived ceramic composites as environmental barrier coatings on steel /." Thesis, Connect to this title online; UW restricted, 2006. http://hdl.handle.net/1773/10562.

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Askestad, Inga. "Ceramic Thermal Barrier Coatings of Yttria Stabilized Zirconia Made by Spray Pyrolysis." Thesis, Norges teknisk-naturvitenskapelige universitet, Institutt for materialteknologi, 2011. http://urn.kb.se/resolve?urn=urn:nbn:no:ntnu:diva-16324.

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A thermal barrier coating (TBC) is used as thermal protection of metallic components exposed to hot gas streams in e.g. gas turbine engines. Due to a high thermal expansion coefficient, low thermal conductivity, chemical- and thermal stability, yttria stabilized zirconia (YSZ) is the most widely used material for TBCs today. In the work presented in this master thesis an aqueous nitrate precursor solution was prepared and deposited on stainless steel substrates by spray pyrolysis to produce 8YSZ coatings (8 mol% of Y2O3 in ZrO2). The precursor solution concentration and deposition parameters,
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Appleby, Matthew P. "High Temperature Damage Characterization Of Ceramic Composites And Protective Coatings." University of Akron / OhioLINK, 2016. http://rave.ohiolink.edu/etdc/view?acc_num=akron1461932405.

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Goat, Christopher. "Erosion resistance in metal - ceramic multilayer coatings for gas turbine compressor applications." Thesis, Cranfield University, 1995. http://dspace.lib.cranfield.ac.uk/handle/1826/10717.

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The erosion resistance of 50 m metal-ceramic multilayer coatings has been investigated under impact conditions comparable to those in a gas turbine compressor cascade. lt was possible to improve upon the erosion resistance of Ti-6Al-4V by a significant margin. The influence of layer mechanical properties, layer thickness, ceramic content and coating process on erosion resistance has been studied over a range of impact conditions. The most suitable coating formulation for maximum erosion resistance changed with particle impact energy. Under low energy impact conditions (<55 joules) coatings wit
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Seraffon, Maud. "Performances of air plasma sprayed thermal barrier coatings for industrial gas turbines." Thesis, Cranfield University, 2012. http://dspace.lib.cranfield.ac.uk/handle/1826/7772.

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Future industrial gas turbines will be required to operate at higher temperatures to increase operating efficiencies and will be subjected to more frequent thermal cycles. The temperatures that the substrates of components exposed in the harshest environments experience can be reduced using air-cooling systems coupled with ceramic thermal barrier coatings (TBCs); however, few studies have been carried out at the substrate temperatures encountered in industrial gas turbines (e.g. 900 – 1000 °C). Better understanding of their behaviour during service and, their various potential failure mechanis
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Ryan, David J. "High temperature degradation of combustion CVD coated thermal barrier coatings." Thesis, Georgia Institute of Technology, 1998. http://hdl.handle.net/1853/18909.

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Jadhav, Amol D. "Processing, characterization, and properties of some novel thermal barrier coatings." Columbus, Ohio : Ohio State University, 2007. http://rave.ohiolink.edu/etdc/view?acc%5Fnum=osu1183851697.

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Books on the topic "Ceramic gas barrier coatings"

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Miller, Robert A. Thermal barrier coatings for gas turbine and diesel engines. NASA, 1990.

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Thermal, Barrier Coating Workshop (1997 Cincinnati Ohio). Thermal Barrier Coating Workshop abstracts. National Aeronautics and Space Administration, 1998.

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SICMAC, Summer School on Layered Functional Gradient Ceramics and Thermal Barrier Coatings (2006 Mahón Spain). Layered, functional gradient ceramics, and thermal barrier coatings: Design, fabrication and applications : proceedings of the SICMAC summer school on layered, functional gradient ceramics, and thermal barrier coatings held in Maó, Menorca Island (Spain) on June 11-16, 2006. Trans Tech Publications Ltd., 2007.

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Bednarz, Piotr. Finite element simulation of stress evolution in thermal barrier coating systems. Forschungszentrum Jülich GmbH, Zentralbibliothek, 2007.

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Thermal Barrier Coating Workshop (1995 NASA Lewis Research Center). Thermal Barrier Coating Workshop: Proceedings of a conference held at and sponsored by NASA Lewis Research Center and cosponsored by DOE and NIST, Cleveland, Ohio, March 27-29, 1995. National Aeronautics and Space Administration, Office of Management, Scientific and Technical Information Program, 1995.

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Center, Lewis Research, ed. Ceramic thermal barrier coatings for electric utility gas turbine engines. National Aeronautics and Space Administration, Lewis Research Center, 1986.

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J, Brindley W., Bailey M. Murray, and United States. National Aeronautics and Space Administration., eds. Thermal barrier coatings for gas turbine and diesel engines. NASA, 1990.

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D, Sheffler K., Ortiz Milton, and Lewis Research Center, eds. Thermal barrier coating life prediction model development: Phase 1, final report. NASA Lewis Research Center, 1989.

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Society, American Ceramic, ed. Progress in thermal barrier coatings. Wiley, 2009.

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R, Choi Sung, Miller Robert A. 1947-, and NASA Glenn Research Center, eds. Thermal fatigue and fracture behavior of ceramic thermal barrier coatings. National Aeronautics and Space Administration, Glenn Research Center, 2001.

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Book chapters on the topic "Ceramic gas barrier coatings"

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Hill, Michael D., Davin P. Phelps, and Douglas E. Wolfe. "Corrosion Resistant Thermal Barrier Coating Materials for Industrial Gas Turbine Applications." In Advanced Ceramic Coatings and Interfaces III. John Wiley & Sons, Inc., 2009. http://dx.doi.org/10.1002/9780470456323.ch10.

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Kell, Joseph, and Heather McCrabb. "Faradayic Process for Electrophoretic Deposition of Thermal Barrier Coatings for Use in Gas Turbine Engines." In Ceramic Transactions Series. John Wiley & Sons, Inc., 2009. http://dx.doi.org/10.1002/9780470522189.ch14.

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Jones, R. L. "Thermal barrier coatings." In Metallurgical and Ceramic Protective Coatings. Springer Netherlands, 1996. http://dx.doi.org/10.1007/978-94-009-1501-5_8.

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Lee, Kang N. "Environmental Barrier Coatings for SiCf/SiC." In Ceramic Matrix Composites. John Wiley & Sons, Inc., 2014. http://dx.doi.org/10.1002/9781118832998.ch15.

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Faucett, D. Calvin, Jennifer Wright, Matt Ayre, and Sung R. Choi. "Foreign Object Damage (FOD) in Thermal Barrier Coatings." In Ceramic Transactions Series. John Wiley & Sons, Inc., 2012. http://dx.doi.org/10.1002/9781118491867.ch25.

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Lee, K. N., D. S. Fox, R. C. Robinson, and N. P. Bansal. "Environmental Barrier Coatings for Silicon-Based Ceramics." In High Temperature Ceramic Matrix Composites. Wiley-VCH Verlag GmbH & Co. KGaA, 2006. http://dx.doi.org/10.1002/3527605622.ch36.

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Leisner, V., A. Lange, P. Mechnich, and U. Schulz. "Magnetron Sputtered Y2SiO5Environmental Barrier Coatings For SIC/SIC CMCS." In Ceramic Transactions Series. John Wiley & Sons, Inc., 2017. http://dx.doi.org/10.1002/9781119407270.ch20.

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Vaßen, R., D. Sebold, and D. Stöver. "Corrosion Behavior of New Thermal Barrier Coatings." In Advanced Ceramic Coatings and Interfaces II. John Wiley & Sons, Inc., 2009. http://dx.doi.org/10.1002/9780470339510.ch4.

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Sun, J. G. "Thermal Imaging Characterization of Thermal Barrier Coatings." In Advanced Ceramic Coatings and Interfaces II. John Wiley & Sons, Inc., 2009. http://dx.doi.org/10.1002/9780470339510.ch6.

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Feuerstein, Albert, Neil Hitchman, Thomas A. Taylor, and Don Lemen. "Process and Equipment for Advanced Thermal Barrier Coatings." In Advanced Ceramic Coatings and Interfaces III. John Wiley & Sons, Inc., 2009. http://dx.doi.org/10.1002/9780470456323.ch9.

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Conference papers on the topic "Ceramic gas barrier coatings"

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Takeuchi, Y. R., and K. Kokini. "Thermal Fracture of Multilayer Ceramic Thermal Barrier Coatings." In ASME 1992 International Gas Turbine and Aeroengine Congress and Exposition. American Society of Mechanical Engineers, 1992. http://dx.doi.org/10.1115/92-gt-318.

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Controlled experiments and a corresponding analytical model were developed to investigate the reasons for crack initiation in multilayer ceramic thermal barrier coatings. The experiments and model determined that surface cracks form as a result of tensile stresses created following stress relaxation in the ceramic at steady state high temperatures (about 900°C-1100°C). Interface cracks generated by out of plane stresses are affected by the presence of these surface cracks and thermal transients and, possibly, edge effects.
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Nagaraj, B. A., A. F. Maricdcchi, D. J. Wortman, J. S. Patton, and R. L. Clarke. "Hot Corrosion Resistance of Thermal Barrier Coatings." In ASME 1992 International Gas Turbine and Aeroengine Congress and Exposition. American Society of Mechanical Engineers, 1992. http://dx.doi.org/10.1115/92-gt-044.

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The hot corrosion resistance of yttria stabilized zirconia (YSZ) thermal barrier coatings was evaluated using an atmospheric burner rig. The coatings were deposited by plasma spraying and electron beam physical vapor deposition (EB-PVD). The tests were performed for up to 2000 hours at 1700°F and 1300°F. The test parameters were designed to simulate the deposit chemistry and corrosion microstructures observed in marine gas turbine engines. The YSZ coating performed very well in the tests, with no spallation and little bond coat corrosion. Plasma sprayed YSZ coating was also evaluated by engine
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Toriz, F. C., A. B. Thakker, and S. K. Gupta. "Thermal Barrier Coatings for Jet Engines." In ASME 1988 International Gas Turbine and Aeroengine Congress and Exposition. American Society of Mechanical Engineers, 1988. http://dx.doi.org/10.1115/88-gt-279.

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Thermal barrier coatings (TBC) have been used in jet engine combustors for over 15 years. However, it is only recently that they have been actively used in the harsh turbine environment on nozzle guide vane platforms. It is intended to use TBCs on vane airfoils, and on rotating turbine blades where the maximum payoff will be realized. Much work has been done in the last five years towards this goal. Problem areas that need to be addressed are as follows: 1. Prevent coating failure due to: a. thermal cycling of the ceramic layer. b. oxidation of the bond coat. c. erosion due to gas stream solid
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Strangman, T. E. "Thermal Strain Tolerant Abradable Thermal Barrier Coatings." In ASME 1991 International Gas Turbine and Aeroengine Congress and Exposition. American Society of Mechanical Engineers, 1991. http://dx.doi.org/10.1115/91-gt-039.

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Thermal barrier coatings (TBCs) are applied to hot gas path surfaces to reduce metal temperatures and thermal stresses for improved turbine component durability. Improvements in engine performance are achieved when TBCs enable reductions in cooling air usage and turbine blade tip-shroud clearances. This paper describes the development of thick TBCs with superior strain tolerance. A pattern of grooves or slant steps incorporated into the surface to be coated enables the development of shadow gaps in the ceramic layer during plasma spray deposition. These gaps segment the TBC, permitting ceramic
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Senturk, Ufuk, Rogerio S. Lima, Carlos R. C. Lima, and Christopher C. Berndt. "Deformation of Plasma Sprayed Thermal Barrier Coatings." In ASME 1999 International Gas Turbine and Aeroengine Congress and Exhibition. American Society of Mechanical Engineers, 1999. http://dx.doi.org/10.1115/99-gt-348.

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The deformation behavior of thermally sprayed partially stabilized zirconia (PSZ) coatings are investigated using Hertzian indentation and four-point bend testing, with in situ acoustic emission monitoring. The experimental deformation curves, together with the corresponding acoustic emission responses and the fracture properties of the material are used in defining the deformation characteristics of the coating (ceramic overlay with metallic bond coal where applicable) and substrate composite system. Experiments are aimed in examining the influence of the bond coat and the coating properties
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Meier, Susan Manning, and Dinesh K. Gupta. "The Evolution of Thermal Barrier Coatings in Gas Turbine Engine Applications." In ASME 1992 International Gas Turbine and Aeroengine Congress and Exposition. American Society of Mechanical Engineers, 1992. http://dx.doi.org/10.1115/92-gt-203.

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Thermal barrier coatings (TBCs) have been used for almost three decades to extend the life of combustors and augmentors and, more recently, stationary turbine components. Plasma sprayed yttria stabilized zirconia TBC currently is bill-of-material on many commercial jet engine parts. A more durable electron beam-physical vapor deposited (EB-PVD) ceramic coating recently has been developed for more demanding rotating as well as stationary turbine components. This ceramic EB-PVD is bill-of-material on turbine blades and vanes in current high thrust engine models and is being considered for newer
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Mutasim, Z. Z., and Y. L. Nava. "Development and Performance Evaluation of Thick Air Plasma Sprayed Thermal Barrier Coatings." In ITSC 2000, edited by Christopher C. Berndt. ASM International, 2000. http://dx.doi.org/10.31399/asm.cp.itsc2000p1325.

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Abstract Air plasma sprayed thermal barrier coatings have been widely used to reduce metal wall temperatures of industrial gas turbine combustor liners. Thermal barrier coatings provide thermal gradients, with the goal of reducing the liner wall temperature to acceptable levels as a result of their low thermal conductivity. A typical thermal barrier coating consists of a 0.1-0.2 mm MCrAlY bond coating and a 0.25-0.35 mm thick 8 wt.% yttria stabilized zirconia ceramic top coating. A method to increase thermal barrier coating effectiveness is the application of thicker ceramic coatings. Developm
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Jordan, Eric H., Maurice Gell, Doug M. Pease, et al. "Bond Strength and Stress Measurements in Thermal Barrier Coatings." In ASME 1997 International Gas Turbine and Aeroengine Congress and Exhibition. American Society of Mechanical Engineers, 1997. http://dx.doi.org/10.1115/97-gt-363.

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The failure mode for thermal barrier coatings in gas turbine engines is spallation at or near the ceramic to metal interface. We propose that the two most important factors leading to this failure are the change in the bond strength and bond stress with cycling. Five methods of measuring stress near the ceramic bond coat interface and four methods of bond strength measurement were investigated. Laser fluorescence and enhanced laboratory x-ray methods have the most potential for stress measurement, while the promising bond strength measurement methods are direct pull testing, chevron notch frac
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Mutasim, Z., C. Rimlinger, and W. Brentnall. "Characterization of Plasma Sprayed and Electron Beam-Physical Vapor Deposited Thermal Barrier Coatings." In ASME 1997 International Gas Turbine and Aeroengine Congress and Exhibition. American Society of Mechanical Engineers, 1997. http://dx.doi.org/10.1115/97-gt-531.

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Laboratory testing was conducted on air plasma sprayed (APS) and electron beam-physical vapor deposited (EB-PVD) thermal barrier coatings (TBCs) applied onto nickel alloy specimens. As-coated chemistry, microstructure, and bond strength of the TBC systems were evaluated. Cyclic oxidation tests that simulated industrial gas turbine environments were also conducted on the various thermal barrier coatings. This study evaluated the effects of ceramic and metallic coating compositions and application processes on coatings microstructure and performance. The relative cyclic performance of the TBC sy
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Aruna, S. T., N. Balaji, and B. Arul Paligan. "A Comparative Study on the Synthesis and Properties of Yttria Stabilized Zirconia (YSZ) and Lanthana Doped YSZ Plasma Sprayed Thermal Barrier Coatings." In ASME 2013 Gas Turbine India Conference. American Society of Mechanical Engineers, 2013. http://dx.doi.org/10.1115/gtindia2013-3563.

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Ceramic thermal barrier coatings (TBCs) have been used for decades to extend the life of combustors and high temperature turbine stationary and rotating components to increase the operating temperature and in turn the performance of gas turbines or diesel engines can be increased. At present, thermal barrier coatings (TBCs) of Y2O3 partially stabilized ZrO2 (YSZ) films are widely used. In recent years ceramic compositions useful in thermal barrier coatings having reduced thermal conductivity are being explored to further increasing the operating temperature of gas turbines and improve the engi
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Reports on the topic "Ceramic gas barrier coatings"

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Sampath, Sanjay. Advanced thermal barrier coatings for operation in high hydrogen content fueled gas turbines. Office of Scientific and Technical Information (OSTI), 2015. http://dx.doi.org/10.2172/1178533.

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Michael Cybulsky. NON-DESTRUCTIVE TECHNIQUES FOR THE EVALUATION OF OVERLAY AND THERMAL BARRIER COATINGS ON GAS TURBINE COMPONENTS. Office of Scientific and Technical Information (OSTI), 1998. http://dx.doi.org/10.2172/778009.

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Functionally graded materials for thermal barrier coatings in advanced gas turbine systems research. Semi-annual report, May 1--December 31, 1996. Office of Scientific and Technical Information (OSTI), 1997. http://dx.doi.org/10.2172/634146.

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