针对燃气轮机叶片气膜孔传统加工方法存在的缺陷,采用飞秒激光旋切带热障涂层的高温合金加工气膜孔,获得了无裂纹、无附着残渣及无重铸层的锥孔。结合飞秒激光加工过程中材料的去除机理,分析得出:等角速度旋切造成的孔锥度较大;材料的去除过程为绝热冷却过程,即与周边材料几乎没有热交换,未发生基体材料熔化后重新凝固形成重铸层的过程。然而,在孔的入口发现黑色附着物,随着加工次数的增加,逐步覆盖整个入口边缘的部分。试验过程中可收集到含有镍、锆、氧等元素的纳米颗粒,证明被去除的材料通过液相爆破的方式以纳米颗粒的形式快速离开基体,从而解释了加工后在孔壁未发现大量附着残渣粘连的原因。相对于低速单层旋切,高速多层旋切加工效率更高。 In view of the defects of conventional gas film hole processing methods for gas turbine blades, the fenestration holes without cracks, non-adhesion residue and no recast layer were obtained by processing femoral holes with high-temperature alloy by femtosecond laser cutting and thermal barrier coating. Combined with the removal mechanism of the material during the femtosecond laser processing, it is concluded that the taper of the hole due to isochronous velocity peeling is larger, the material removal process is adiabatic cooling process, that is, there is almost no heat exchange with the surrounding material, and no melting of the base material occurs After re-solidified to form a recast layer process. However, a black attachment was found at the entrance to the hole, gradually covering the entire edge of the entrance as the number of processes increased. During the test, nanoparticles containing elements such as nickel, zirconium and oxygen could be collected to prove that the removed material quickly separated from the matrix in the form of nano-particles by liquid-phase explosion, which explained that no large amount of adhesion was observed in the pore walls after processing Residue adhesion causes. Relative to low-speed single-layer peeling, high-speed multi-layer peeling processing more efficient.