Abstract
Turbine blades (rotary parts) and vanes (stationary components) are made from nickel-based superalloys. The replacement of high-cost aviation/industrial blades and vanes is the most important task in the turbojet engine repair industry. These parts which are manufactured by the investment casting process withstand high temperatures and high stresses/strains during the service. Depending on the temperature and strain rate, creep failure occurs by various mechanisms in superalloys. Cavitation is one of the modes of creep failure. In order to facilitate creep life extension of hot section parts and reduce overhaul of engine costs, alloy rejuvenation procedures have been investigated and implemented over the past few years. This study introduces a method including hot isostatic pressing (HIPing) and a post-HIP heat treatment for recovering the creep strength of the cast polycrystalline nickel-based superalloy Rene®80. To certify the positive effect of introduced method on the renovation of creep properties, the creep rupture tests at 850±1 °C/360±2 MPa were assessed. As revealed by the results of this evaluation, the creep properties of Rene®80 can be recovered by HIP procedure (1205 °C /150MPa /4 h) in combination with a post-HIP heat treatment (1093 °C /4hr + 1054 °C /4hr + 845 °C /24hr).
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Barjesteh, M.M. Rejuvenation of Nickel-Based Superalloy Experiencing Creep via Use of Hot Isostatic Pressing and Heat Treatment. Inter Metalcast 16, 1960–1975 (2022). https://doi.org/10.1007/s40962-021-00739-9
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DOI: https://doi.org/10.1007/s40962-021-00739-9