Thermoplastic fiberglass has been compression molded in the shape of thick panels with the nominal thickness of 10 mm and the size of 300x300 mm2. A simplified procedure has been adopted to speed up the lamination procedure, and making it adapt to the aim of recycling waste glass fiber fabrics and thermoplastics films. Low density polyethylene has been used as matrix to simplify the laboratory activities, but the same procedure can be extended to any other thermoplastic film, such as polyamide. The final thermoplastic composite shows unique properties in terms of repairability and improves its performances by increasing the number of repairing steps. For this aim, a repairability test has been designed in the bending configuration, and 3 consecutive cycles of bending/repairing/bending have been carried out. Static mechanical properties were, instead, low in comparison with traditional fiberglass, because of the choice of a polyethylene matrix. Bending tests have shown that the maximum strength is lower than 10 MPa and the elastic modulus less than 1 GPa. Nevertheless, the toughness of the thermoplastic composite was very high, and the samples continued to deform under bending for any displacement.

K417G Ni-based superalloy is widely used in aeroengine turbine blade for its excellent properties. However, the aeroengine rotor blade zigzag crown appears early failure frequently, which is because of the wear problems occurring in the working process. Laser forming repairing (LFR) is a promising technique to repair these damaged blades. Unfortunately, the laser formed Ni-based superalloys with high content of (Al + Ti) have a high cracking sensitivity. In this paper, the crack characterization of the LFRed K417G, the microstructure, microhardness and tribological properties of the coating before and after laser remelting are presented. The results show that the microstructure of as-deposited K417G consists of γ phase, γ′ precipitated phase, γ + γ′ eutectic and carbide. Cracking mechanisms including solidification cracking, liquation cracking and ductility dip cracking are proposed based on the composition of K417G and processing characteristics to explain the cracking behavior of the K417G superalloy during LFR. After laser remelting, the microstructure of the coating has been refined, and the microhardness and tribological properties has been improved. Laser remelting can decrease the size of the cracks in the LFRed K417G but not the number. Therefore, laser remelting can be applied as an effective method for strengthening coating and as an auxiliary method for controlling cracking.