The application of compressor blisk is one of the typical technologies of high-performance engines. However, due to its contact with high-speed airflow containing various solids, a variety of different forms of structural damage and performance degradation occur frequently, which seriously restricts the high performance, high reliability, and long-life operation of the engine. The remanufacturing technology of blisk based on repair is an effective way to solve the above problems. Aiming at the common basic problems in the process of repair and remanufacture of compressor blisk, this paper summarizes the historical evolution and technology development on the repairing and remanufacturing technology of blisk at home and abroad. According to the damage forms of geometric structure and service function, the damage reparable evaluation and design, fusion welding repair technology, pressure welding repair technology, brazing and laser beam additive manufacturing, surface treatment and optimization/strengthening technology are systematically expounded. The important issues such as the assessment and design, the development of technologies, and deep repair in the remanufacture of the blisk are explored in order to promote the rapid development and successive application of blisk remanufacturing technology.

The lifetime of Si bond coatings in environmental barrier coatings is constrained by phase-transition-induced cracking of the SiO₂ scale. In this study, Si–HfO₂ dual-state duplex composite materials are proposed to address this issue by partially forming HfSiO₄ and minimizing the SiO₂ content. The as-prepared composite exhibited a structure comprising discrete HfO₂ “bricks” embedded in a continuous Si “mortar”, while the oxidized state transformed into discrete HfSiO₄ “bricks” within continuous thin SiO₂ “mortars”. The results indicate that continuous thin SiO₂ contributes to reducing the oxidation rate to a level comparable to that of pure Si, and discrete HfSiO₄ particles aid in relieving phase transition-induced stress and inhibiting crack propagation, thereby enhancing oxidation and cracking resistance simultaneously. Consequently, the composite with 20 mol% HfO₂ and a mean particle size of ~500 nm at 1370 ℃ exhibited a service lifetime 10 times greater than that of pure Si. This research provides valuable insights for designing Si-based bond coatings with improved service lifetime.

Electromagnetic wave-absorbing (EMA) materials at high temperatures are limited by poor conduction loss (L_c). However, adding conductors simultaneously increases the conduction loss and interfacial polarization loss, leading to a conflict between impedance matching (Z_in/Z₀) and electromagnetic wave loss. This will prevent electromagnetic waves from entering the EMA materials, finally reducing overall absorbing performance. Here, the effective electrical conductivity (σ) is enhanced by synchronizing particle size and grain number of Ti₃AlC₂ to increase the conduction loss and avoid the conflict between the impedance matching and the electromagnetic wave loss. As a result, the best-absorbing performance with an effective absorption bandwidth (EAB) of 4.8 GHz (10.6–15.4 GHz) at a thickness of only 1.5 mm is realized, which is the best combination of wide absorption bandwidth and small thickness, and the minimum reflection loss (RL_min) reaches −45.6 dB at 4.1 GHz. In short, this work explores the regulating mechanism of the EMA materials of effective electrical conductivity by simulated calculations using the Vienna ab-initio Simulation Package (VASP) and COMSOL as well as a series of experiments, which provide new insight into a rational design of materials with anisotropic electrical conductivity.

The unique columnar structure endows thermal barrier coatings (TBCs) prepared by plasma spray-physical vapor deposition (PS-PVD) with high thermal insulation and long lifetime. However, the coating delamination failure resulting from an intra-column fracture (within a column rather than between columns) is a bottleneck in the solid dust particle impact environment for aero-engine. To clarify the intra-column fracture mechanism, a basic layer deposition model is developed to explore a heterogeneous weak-to-strong layered structure formed by a local transient in-situ deposit temperature. During the PS-PVD, an in-situ deposit surface is continuously updated due to constantly being covered by vapor condensation, showing a transient temperature, which means that the in-situ deposit surface temperature rises sharply in short period of 0.2 s of depositing a thin layer during a single pass. Meanwhile, the increasing temperature of the in-situ deposit surface results in an experimentally observed heterogeneous weak-to-strong structure, showing a continuous transition from a porous weak structure at the bottom region to a dense strong structure at the top region. This structure easily makes the intra-column fracture at the porous weak region. The results shed light on improving TBC lifetime by restraining the intra-column fracture.

Thermal barrier coatings (TBCs) can effectively protect the alloy substrate of hot components in aeroengines or land-based gas turbines by the thermal insulation and corrosion/erosion resistance of the ceramic top coat. However, the continuous pursuit of a higher operating temperature leads to degradation, delamination, and premature failure of the top coat. Both new ceramic materials and new coating structures must be developed to meet the demand for future advanced TBC systems. In this paper, the latest progress of some new ceramic materials is first reviewed. Then, a comprehensive spalling mechanism of the ceramic top coat is summarized to understand the dependence of lifetime on various factors such as oxidation scale growth, ceramic sintering, erosion, and calcium-magnesium-aluminium-silicate (CMAS) molten salt corrosion. Finally, new structural design methods for high-performance TBCs are discussed from the perspectives of lamellar, columnar, and nanostructure inclusions. The latest developments of ceramic top coat will be presented in terms of material selection, structural design, and failure mechanism, and the comprehensive guidance will be provided for the development of next-generation advanced TBCs with higher temperature resistance, better thermal insulation, and longer lifetime.

Thermally sprayed coatings are essentially layered materials and contain large numbers of lamellar pores. It is thus quite necessary to clarify the formation mechanism of lamellar pores which significantly influence coating performances. In the present study, to elaborate the formation mechanism of lamellar pores, the yttria-stabilized zirconia (ZrO₂–7 wt% Y₂O₃, 7YSZ) splats, which have high fracture toughness and tetragonal phase stability, were employed. Interestingly, anomalous epitaxial growth occurred for all deposition temperatures in spite of the extremely high cooling rate, which clearly indicated chemical bonding and complete contact at splat/substrate interface before splat cooling. However, transverse spallation substantially occurred for all deposition temperatures in spite of the high fracture toughness of 7YSZ, which revealed that the lamellar pores were from transverse cracking/spallation due to the large stress during splat cooling. Additionally, fracture mechanics analysis was carried out, and it was found that the stress arose from the constraint effect of the shrinkage of the splat by locally heated substrate with the value about 1.97 GPa. This clearly demonstrated that the stress was indeed large enough to drive transverse cracking/spallation forming lamellar pores during splat cooling. All of these contribute to understanding the essential features of lamellar bonding and further tailoring the coating structures and performance.

Thermal barrier coatings (TBCs) enable the hot section part to work at high temperatures owing to their thermal barrier effect on the base metal components. However, localized spallation in the ceramic top-coat might occur after long duration of thermal exposure or thermal cycling. To comprehensively understand the damage of the top-coat on the overall hot section part, effects of diameter and tilt angle of the spallation on the temperature redistribution of the substrate and the top-coat were investigated. The results show that the spallation diameter and tilt angle both have a significant effect on the temperature redistribution of the top-coat and the substrate. In the case of the substrate, the maximum temperature increment is located at the spallation center. Meanwhile, the surface (depth) maximum temperature increment, having nothing to do with the tilt angle, increases with the increase of the spallation diameter. In contrast, in the case of the top-coat, the maximum temperature increment was located at the sharp corner of the spallation area, and the surface (depth) maximum temperature increment increases with the increase of both the spallation diameter and the tilt angle. Based on the temperature redistribution of the substrate and the top-coat affected by the partial spallation, it is possible to evaluate the damage effect of spalled areas on the thermal capability of TBCs.