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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100J/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。
The nickel-based superalloy FGH95 powder was used to laser repair the GH4169 alloy, a common material of aeroengine, to test the high temperature tensile properties of the samples under different process parameters and to analyze the fracture mechanism. The results show that under the proper process parameters, the tensile strength of the repaired sample can reach more than 85% of the non-destructive sample. When the energy density of the laser line is 100J / mm2, the tensile strength of the repaired sample reaches the maximum value 708 MPa, which is 90.4% of the non-destructive sample, the yield strength also reached the maximum of 538 MPa, exceeding 4.3% of the non-destructive sample. The hot tensile fracture location of the repaired specimen is located in the heat-affected zone of the substrate. Elemental segregation in the heat-affected zone is the main reason for the high-temperature tensile properties of the repaired sample under the cyclic heat generated by the laser beam irradiation .