Abstract
The irreversible structural changes of the single-crystal ZhS32-VI nickel superalloy blades of a high-pressure turbine that occur during life tests of a gas turbine engine are studied. The main operation damages in the hottest section of the blade airfoil are found to be the fracture of the heat-resistant coating in the leading edge and the formation of thermomechanical fatigue cracks. The possibility of reconditioning repair of the blades is considered.
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Original Russian Text © O.G. Ospennikova, M.R. Orlov, V.G. Kolodochkina, R.M. Nazarkin, 2014, published in Deformatsiya i Razrushenie Materialov, 2014, No. 8, pp. 22–29.
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Ospennikova, O.G., Orlov, M.R., Kolodochkina, V.G. et al. Structural changes and damage of single-crystal turbine blades during life tests of an aviation gas turbine engine. Russ. Metall. 2015, 324–331 (2015). https://doi.org/10.1134/S0036029515040114
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DOI: https://doi.org/10.1134/S0036029515040114