Submission Deadline: 31 March 2023 (closed) View: 137
The development of advanced aero engines is linked with increasing turbine inlet temperature, which results in harsher operating environment for turbine blades. The turbine inlet temperature has reached approximate 2000 K, far exceeding the work temperature limit (~1400 K) of nickel-based superalloys that provide load bearing capacity for the turbine blades. To maintain adequate strength and achieve required lifetime, modern turbine blades are composed of nickel-based single crystal superalloy as substrate in combination with thermal barrier coating (TBC) and complex cooling system. TBC provides protection from the harsh environment and prolongs the component life. However, the application of TBC brings new challenges. The TBC is subjected to both external loads (e.g., high temperature, time-varying gas environment, and mechanical load transferred from the blade substrate through deformation) and internal loads (e.g., stress caused by the mismatch of thermal expansion of each layer, and the TGO growth). As a consequence of the TBC potential spallation caused by the loads, the nickel-based superalloy substrate would be exposed to the aggressive operating conditions exceeding its damage resistance limit, which could result in the overheat and fracture of turbine blades. Therefore, the evaluation of the TBC’s durability has become a critical issue limiting the application of TBC in turbine blades. Recently the TBC-related materials and processes have gained remarkable advance, which require better knowledge and understanding of the mechanics behavior, failure mechanisms and durability-determined life of TBC. It is hoped that this special issue could contribute to facilitating the communication and dissemination of the recent development of strength theory, numerical methods, and experimental techniques for TBC, thereby promoting the improvement and applications of TBC in advanced turbines
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