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Tytuł artykułu

Degradation of the gas turbine blade coating and its influence on the microstructure state of the superalloy

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Języki publikacji
EN
Abstrakty
EN
The technical condition of the blades has a critical influence on the reliability and life span of a gas turbine and an engine into which it is built in. The main causes of blade damage are overheating, creeping, thermal fatigue, high temperature corrosion, etc. It is often caused by adverse operational conditions or manufacturing defect, e.g. using insufficiently durable types of heat-resistant protective coatings or applied in an improper manner on the blade material. Reaction of coatings and blade material to mechanical and thermal loads depends mainly on the operating temperature of the turbine. Selection of a protective coating and material to manufacture a blade with an assumed strength must take into account its mechanical and thermal properties at maximum aerofoil temperature. The article presents characteristic forms of operational damages to the gas turbine blades of a turbojet aero engine. Distinguished were operational factors and their influence on the technical condition of coatings during the engine operation period. An influence of excess exhaust gas temperature on the condition of the heat-resistant blade layer was shown. Shown were also results of morphology tests of coating degradation types. Results of micro-structure tests of the blade superalloy after damage to the heat-resistant coating were also presented.
Słowa kluczowe
Twórcy
autor
  • Air Force Institute of Technology Ksiecia Bolesława Street 6, 01-494 Warsaw, Poland tel.: +48 600 820 841, +48 604 118 918
autor
  • Air Force Institute of Technology Ksiecia Bolesława Street 6, 01-494 Warsaw, Poland tel.: +48 600 820 841, +48 604 118 918
autor
  • Military University of Technology Kaliskiego Street 2, 00-908 Warszawa, Poland tel.: +48 261 83-93-49
Bibliografia
  • [1] Bessler, W. G., Schulz, C., Lee, T., Jeffries, J. B., Hanson, R. K., Laser-induced fluorescence detection of nitric oxide in high-pressure flames with A-X (0,1) excitation, Proceedings of the Western States Section of the Combustion Institute, Spring Meeting, pp. 145-156, Oakland 2001.
  • [2] Błachnio, J., Analysis of causes of decohesion of a gas turbine blade made of EI-867WD alloy, Aircraft Engineering and Aerospace Technology: An International Journal, Vol. 83, No. 1, pp.14-20, 2011.
  • [3] Błachnio, J., Dięgielewski, W., Kułaszka, A., Zasada, D., The influence of exploitative factors on the heatproof layer of gas turbine’s blades, Studies and Proceedings of Polish Association for Knowledge Management, No. 68, pp. 17-31, 2014.
  • [4] Buckmaster, J., Clavin, P., Linan, A., Matalon, M., Peters, N., Sivashinsky, G., Williams, F.A., Combustion theory and modeling, Proceedings of the Combustion Institute, Vol. 30, pp. 1-19, Pittsburgh 2005.
  • [5] Corcione, F. E., et al., Temporal and Spatial Evolution of Radical Species in the Experimental and Numerical Characterization of Diesel Auto-Ignition, Proceedings of The Fifth International Symposium on Diagnostics and Modeling of Combustion in Internal Combustion Engines (COMODIA 2001), pp. 355-363, Nagoya 2001.
  • [6] Góral, M., et al., Diffusion sluminide coatings for TiAl intermetallic turbine blades, Intermetallics 19, pp. 744-747, 2011.
  • [7] Hejwowski, T., Modern layers thermally covered resistant to abrasive and erosive use, Lublin University of Technology, Lublin 2013.
  • [8] Kułaszka A., Giewoń J., Technical Minutes from Research: No. 28/RD-33/2014, No.7/RD-33/2015, No. 30/RD-33/2015 and No. 38/RD-33/2015, ITWL, Warszawa (unpublished).)
  • [9] Mendala, B., Establishement of structures and properties of protective coatings on steal blades of aircraft engines’ compressors, Silesian University of Technology, Gliwice 2013.
  • [10] Moskal, G., Microstracture and properties of sprayed with plasma thermal layer barriers on the base of gadolinium yirconate, Silesian University of Technology, Gliwice 2012.
  • [11] Sieniawski, J., Criteria and methods for acceptance of materials for components of avionic turbojet engines, Technical University of Rzeszów, 1995.
  • [12] Swadźba, L., et al., Characterization of microstructure and properties of TBC systems with gradient of chemical composition and porosity, Archives of Metallurgy and Materials 53, pp. 945-954, 2008.
  • [13] Szczepanik, R., Błachnio, J., Swadźba, L., Opracowanie technologii nanoszenia powłok ochronnych TBC, Raport ITWL, Warszawa 2001.
Typ dokumentu
Bibliografia
Identyfikator YADDA
bwmeta1.element.baztech-06131898-12f1-4ab8-869e-1ac76c6df6be
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