为满足新一代航空发动机更高推重比的设计要求，层板结构逐渐成为研究热点。 GH4099 和 GH3128 作为典型的镍基高温合金，因其优异的高温强度、抗氧化和抗蠕变性能，被广泛应用于层板结构。 然而，直接扩散焊易产生孔洞和碳化物缺陷，导致接头强度低。 因此，本研究通过添加 3 μm Ni 箔中间层，系统研究扩散焊温度(1 040~1 160 ℃)对GH4099/GH3128 接头界面组织和力学性能的影响规律， 以优化工艺参数并提升接头力学性能。 采用扫描电子显微镜(SEM)和拉伸测试表征微观组织和力学性能。结 果 表 明，Ni 中间层能有效消除界面孔洞，同 时 Ni 对 C 元 素 的 固 溶作用使接头界面产生贫碳区；GH3128 侧析出含 W、Mo 的碳化物，GH4099 侧有少量 γ′相生成； 焊接参数为 1 120 ℃-10 MPa-60 min 时接头力学性能最优，抗拉强度达到 938 MPa，断后伸长率为 17%。

To meet the design requirements of higher thrust-to-weight ratios for the new generation of aeroengines,laminate structures have gradually become a research hotspot. GH4099 and GH3128, as typical nickel-based superalloys,are widely used in laminate structures because of their excellent high-temperature strength, oxidation resistance and creepresistance. However, direct diffusion bonding is prone to produce pores and carbide defects, resulting in low joint strength.Therefore, this study aims to systematically investigate the influence of diffusion bonding temperature (1 040~1 160 ℃) onthe microstructure and mechanical properties of GH4099/GH3128 joints by adding a 3 μm Ni foil interlayer to optimize theprocess parameters and improve the mechanical properties of the joints. The microstructure and mechanical properties werecharacterized by scanning electron microscopy (SEM) and tensile tests. The results show that the Ni interlayer caneffectively eliminate interface pores, and the solid solution effect of Ni on C causes a carbon-poor zone to form at the jointinterface; carbides containing W and Mo precipitate on the GH3128 side, and a small amount of the γ′ phase is generatedon the GH4099 side; when the bonding parameters are 1 120 ℃-10 MPa-60 min, the mechanical properties of the joint areoptimal, with a tensile strength of 938 MPa and an elongation of 17%.