22 X Q Chen,Z M Gong.H Huang,SZ Ge,and L B Zhou these parts instead of scrapping them.The repairing process starts with cleaning and covering the defective areas with the braze material.The purpose of brazing is to fill up the defects,but unavoidably,the brazed areas will be higher than the original surface.Figure 2 shows a cross section of the airfoil brazed with a repair material. inner buttress outer buttress featherseal slots airfoils baffle (concave side) inner platform outer platform concave side of mateface mounting lugs Figure 1 Schematics of a HPT Vane. Leading edge Cavities Cooling holes Trailing edge Braze material Parent material Figure 2 Turbine airfoils repaired with braze material. Table 1 summarises the overhaul conditions of typical jet engine high- pressure turbine vanes.The wall thickness of the airfoil ranges from 0.8 mm in the trailing edge to 2 mm in the leading edge.The braze material, similar to the parent material in composition,is laid down on the airfoils manually,and its thickness is about I mm.The compositions of the braze22 X Q Chen, Z M Gong, H Huang, S Z Ge, and L B Zhou these parts instead of scrapping them. The repairing process starts with cleaning and covering the defective areas with the braze material. The purpose of brazing is to fill up the defects, but unavoidably, the brazed areas will be higher than the original surface. Figure 2 shows a cross section of the airfoil brazed with a repair material. Figure 1 Schematics of a HPT Vane. Braze material Parent material Leading edge Trailing edge Cavities Cooling holes Figure 2 Turbine airfoils repaired with braze material. Table 1 summarises the overhaul conditions of typical jet engine high￾pressure turbine vanes. The wall thickness of the airfoil ranges from 0.8 mm in the trailing edge to 2 mm in the leading edge. The braze material, similar to the parent material in composition, is laid down on the airfoils manually, and its thickness is about 1 mm. The compositions of the braze