Ceramic materials in aviation engineering (review)

Evdokimov S.A., Shchegoleva N.E., Sorokin O.Ju.
UDC
678.84
DOI
10.18577/2307-6046-2018-0-12-54-61
Article PDF (Russian) (658.14 KB)
How to cite
Evdokimov S.A., Shchegoleva N.E., Sorokin O.Ju. Ceramic materials in aviation engineering (review) // Proceedings of VIAM. 2018. No. 12. DOI: 10.18577/2307-6046-2018-0-12-54-61. URL: https://test.viam.ru/en/journal/2018/12/6
Keywords
ceramics, gas turbine engine, combustion chamber, strength, ceramic-matrix composites, heat-shielding coatings.
Abstract

Increasing demand for powerful gas turbine and propulsion engines leads to harsher operational conditions (i.e., higher temperature, speed, more tension, aggressive environments, etc.) which in turn require complex processing decisions. Increased efficiency of aircraft engines has been achieved by new design scheme, development of advanced materials and technologies.

The use of ceramic thermal barrier coatings enabled to increase the temperature in hot areas of gas turbines to the maximum value of higher than 1500 °C thus resulting in superior engine performance and efficiency. Although ceramic matrix composites (CMCs) are still prospective materials for the use in gas turbines, their implementation is around the corner due to their improved toughness compared to monolithic ceramics, higher temperature and lower density compared to superalloys.

CMCs are likely to be envisaged for middle and large-sized gas turbine engines as structural material for simple-shaped and thin components like burner linings, sealings, shrouds, etc.

This article highlights the studies on ceramic materials with the «self-healing» effect. It was shown that the use of CMCs with a «self-healing» ability enables elimination of small defects originating during the engine work, thus there is no necessity for landing, emergency engine stops, repairs, etc. In the beginning «self-healing» effect took around 1000 hours, but then researchers shortened the time to a minute at 1000oC by adding a small amount of Mn which in their understanding helps to promote such an ability.

Reference list
  1. Deev I.S., Kablov E.N., Kobets L.P., Chursova L.V. Issledovanie metodom skaniruyushhej elektronnoj mikroskopii deformacii mikrofazovoj struktury polimernyh matric pri mehanicheskom nagruzhenii [Research of the scanning electron microscopy method deformation of microphase structure of polymeric matrix at mechanical loading] // Trudy VIAM: elektron. nauch-tehnich. zhurn. 2014. №7. St. 06. Available at: http://www.viam-works.ru (accessed: April 02, 2018). DOI: 10.18577/2307-6046-2014-0-7-6-6.
  2. Rozenenkova V.A., Kablov E.N., Solntsev St.S., Mironova N.A. Polifunktsionalnyye zashchitnyye tekhnologicheskiye pokrytiya (ZTP) dlya izotermicheskoy shtampovki na vozdukhe v rezhime sverkhplastichnosti diskov iz superzharoprochnykh nikelevykh splavov [Polyfunctional protective technological coatings (PTC) for isothermal punching in air in the mode of superplasticity of disks made of super-strong nickel alloys] // Sb. dokl. konf. «Sovremennyye vysokotemperaturnyye kompozitsionnyye materialy i pokrytiya». M.: VIAM, 2013. S. 10.
  3. Kablov E.N., Ospennikova O.G., Vershkov A.V. Redkie metally i redkozemelnye elementy – materialy sovremennyh i budushhih vysokih tehnologij [Rare metals and rare earth elements – materials of modern and future high technologies] // Trudy VIAM: elektron. nauch.-tehnich. zhurn. 2013. №2. St. 01. Available at: http://www.viam-works.ru (accessed: March 23, 2018).
  4. Kablov E.N., Ospennikova O.G., Svetlov I.L. Vysokoeffektivnoe ohlazhdenie lopatok goryachego trakta GTD [Highly efficient cooling of GTE hot section blades] // Aviacionnye materialy i tehnologii. 2017. №2 (47). S. 3–14. DOI: 10.18577/2071-9140-2017-0-2-3-14.
  5. Kablov E.N., Bondarenko Yu.A., Echin A.B. Razvitiye tekhnologii napravlennoy kristallizatsii liteynykh vysokozharoprochnykh splavov s peremennym upravlyayemym temperaturnym gradiyentom [Development of technology of cast superalloys directional solidification with variable controlled temperature gradient] // Aviacionnyye materialy i tehnologii. 2017. №S. S. 24–38. DOI: 10.18577/2071-9140-2017-0-S-24-38.
  6. Karimbayev T.D., Luppov A.A., Afanasyev D.V., Palchikov D.S. O formirovanii tekhnicheskikh trebovaniy na polimernyy material perspektivnoy rabochey lopatki ventilyatora TRDD [On the formation of technical requirements for polymer material of a promising working blade of a turbofan] // Dvigatel. 2015. №1 (97). S. 2–8.
  7. Karimbayev T.D., Luppov A.A., Afanasyev D.V. Rabochiye lopatki ventilyatorov iz ugleplastika dlya perspektivnykh dvigateley [Working blades of carbon fiber fans for advanced engines] // Dvigatel. 2011. №6 (78). S. 2–9.
  8. Eaton H.E., Linsey G.D., Sun E.Y. et al. EBC Protection of SiC/SiC Composites in the Gas Turbine Combustion Environment-Continuing Evaluation and Refurbishment Considerations // ASME Proceedings. Ceramic. 2001. Paper No. 2001-GT-0513.
  9. Paul A., Jayaseelan D.D., Venugopal S. UHTC composites for hypersonic applications // American Ceramic Society Bulletin. 2012. Vol. 91. No. 1. P. 22–29.
  10. Bongiorno A., Först C.J., Kalia R.K. A Perspective on Modeling Materials in Extreme Environments: Oxidation of Ultrahigh-Temperature Ceramics // MRS Bulletin. 2006. Vol. 31. Р. 410–418.
  11. Justin J.F., Jankowlak A. Ultra High Temperature Ceramics: Densification, Properties and Thermal Stability // Aerospace Lab. 2011. Is. 03–08. P. 1.
  12. Zhestkov B.E., Terentyeva V.S. Issledovaniye mnogofunktsionalnogo pokrytiya MAI D5, prednaznachennogo dlya zashchity osobozharoprochnykh materialov [Study of the multifunctional coating MAI D5, intended for the protection of extra heat-resistant materials] // Metally. 2010. №1. S. 39–48.
  13. Solntsev S.S., Shalin R.e., Isayeva N.V. Reaktsionnospekayemyye keramicheskiye pokrytiya [Reactable ceramic coatings] // Sb. tr. 8-y Vsemir. konf. po keramike i novym materialam. 1995. T. 9. S. 237–242.
  14. Cabet C. Review: Oxidation of SiC/SiC Composites in Low Oxidizing and High Temperature Environment // Materials Issues for Generation IV Systems. 2008. Р. 351–366.
  15. Solntsev S.S., Isayeva N.V., Shvagireva V.V., Maksimov V.I. Vysokotemperaturnye pokrytiya dlya zashchity splavov i uglerodkeramicheskikh kompozitsionnykh materialov ot okisleniya [High-temperature coatings for the protection of alloys and carbon-ceramic composite materials from oxidation] // Konversiya v mashinostroyenii. 2004. №4. S. 77–80.
  16. Ceramic matrix composites take flight in LEAP jet engine. Available at: https://phys.org/news/2017-01-ceramic-matrix-composites-flight-jet.html#jCphttps://phys.org/news/2017-01-ceramic-matrix-composites-flight-jet.html (ac-cessed: March 22, 2018).
  17. Takeda M., Sakamoto J., Saeki A., Imai Y., Ichikawa H. High Performance Silicon Carbide Fiber Hi-Nicalon for Ceramic Matrix Composites // Ceramic Engineering and Science Proceedings. 2005. Vol. 16 (4). P. 37–44.
  18. Ichikawa H. High Performance SiC Fibers from Polycarbosilane for High Temperature Applications, Key Engineering Materials. 2007. Vol. 352. P. 59–64. DOI: 10.4028/www.scientific.net/KEM.352.59.
  19. Yun H.M., Wheeler D., Chen Y., DiCarlo J.A. Thermo-Mechanical Properties of Super, Sylramic SiC Fibers // Ceramic Engineering and Science Proceedings. 2005. Vol. 26 (2). P. 59–65. Available at: https://doi.org/10.1002/9780470291221.ch8 (accessed: March 22, 2018).
  20. Ishikawa T. Advances in Inorganic Fibers // Advances in Polymer Science. 2005. Vol. 178. P. 109–144. DOI: 10.1007/b104208.
  21. Van Roode M., Price J., Kimmel J. et al. Ceramic Matrix Composite Combustor Liners: A Summary of Field Evaluations // Journal of Engineering for Gas Turbines and Power. 2005. Vol. 129 (1). P. 21–30. DOI:10.1115/1.2181182.
  22. Self-Repairing Ceramic Eyed For Aircraft Engines, Shinkansen. Available at: https://www.japanbullet.com/features/self-repairing-ceramic-eyed-for-aircraft-engines-shinkansen (accessed: March 23, 2018).