采用镍基高温合金FGH95粉末对航空发动机常用材料GH4169合金进行激光修复试验，测试不同工艺参数下修复试样的高温拉伸性能并对其断裂机理进行分析。研究表明，在合适的工艺参数下，修复试样的高温抗拉强度可达到无损试样的85%以上；当激光线能量密度为100 J/mm2时，修复试样的高温抗拉强度达到最大值708 MPa，为无损试样的90.4%，其屈服强度也达到最大值538 MPa，超过无损试样的4.3%。修复试样的高温拉伸断裂位置位于基体的热影响区，在激光束照射所产生的交变循环热作用下，热影响区发生的元素偏析是导致修复试样高温拉伸性能下降的主要原因。

Laser repair of GH4169 alloy which is commonly used in aero engines by usage of the nickel-based superalloy FGH95 powder is tested. The high-temperature tensile properties of the repaired sample with different process parameters are investigated and the fracture mechanism is also analyzed. The results show that, with appropriate process parameters, the high-temperature tensile strength of the repaired samples can be recovered up to more than 85% of that of the intact samples. When the laser linear energy density is 100 J/mm2, the maximum high-temperature tensile strength is 708 MPa, which is 90.4% of that of the intact sample and the maximum yield strength is 538 MPa, which exceeds 4.3% of that of the intact sample. The fractions of the repaired samples occur at the substrate heat-affected zone, where the segregation of elements is induced by the alternating heat action of laser scanning. This segregation is the main reason for the degradation of the high-temperature tensile property of the repaired samples.