采用选区激光熔化(selective laser melting，SLM)工艺制备了TiN/Inconel 718 (IN718)复合材料，利用OM、SEM、EDS、EBSD以及XRD等手段研究了SLM成形态和不同热处理条件下TiN/IN718复合材料的微观组织和力学性能。结果表明：SLM成形态TiN/IN718复合材料中TiN颗粒与基体之间紧密结合，并形成了约为0.3 μm厚的过渡层，与IN718合金相比，TiN/IN718复合材料的显微硬度和拉伸强度均有明显改善(分别提高39 HV_0.2和74 MPa)。双时效(DA)和固溶时效(SA)热处理的TiN/IN718复合材料中，强化相的析出和TiN颗粒的存在导致裂纹萌生源增多，从而造成强度没有得到明显提升。均匀化 + 固溶时效(HSA)热处理后材料发生了完全再结晶，晶粒内部析出了超细球状的γ'/γ''强化相，晶界处和晶粒内部TiN颗粒周围的针状δ相含量增加。因此，经过HSA处理后材料的抗拉强度有显著提升，达到1430 MPa (提高了410 MPa)。

The Inconel 718 alloy has become a remarkable candidate material for aerospace jet engines, turbine blades, and some other elevated temperature components owing to its superior tensile strength, anticorrosion and thermal performance. Moreover, TiN ceramic particles with high hardness and chemical stability have been realized to significantly improve the mechanical properties of the alloy matrix at a low content. Accordingly, in this work, the Inconel 718 (IN718) alloy and TiN/IN718 composite were fabricated by the optimized selective laser melting (SLM) process. Further, the microstructures and mechanical properties of the IN718 alloy and TiN/IN718 composite under heat treatments were investigated, respectively. The results show that the TiN particles were highly combined with the matrix, and a transition layer with 0.3 μm was formed in the SLM-fabricated TiN/IN718 specimens. Additionally, the microhardness and tensile strength were significantly improved compared with IN718 alloy (39 HV_0.2, 74 MPa, respectively). After the double aging and solution aging (SA) treatments, the number of crack initiation sources was increased owing to the precipitation of the δ phase, which deteriorated the tensile strength of the TiN/IN718 composite. After the homogenization + SA (HSA) treatment, the composite was completely recrystallized, and an appropriate amount of needle- and plate-like δ phases precipitated at the grain boundaries. Hence, the TiN/IN718 composite after the HSA treatment exhibited optimally comprehensive mechanical properties.