先进航空发动机用机匣等高温合金构件不断向结构复杂化和薄壁轻量化发展，易导致充型困难、组织不均匀和凝固缺陷等问题，对该类铸件的精密铸造技术和工艺控制提出了新的挑战。 针对上述问题，文中比较了常规铸造工 艺与热控凝固工艺下 K4169 合金薄壁变截面特征件的充型情况、缩松、组织以及力学性能，并对热控凝固工艺参数进行 了探索。 结果表明，在常规铸造工艺下，特征件薄壁部位的充型率仅为 26%，变截面部位出现了缩松。 采用浇注温度为 1 360 ℃的热控凝固工艺可以使铸件薄壁部位的充型面积提高 226%，显著减少铸件中的缩松，获得了细小的晶粒组织，平均晶粒尺寸为 624 μm，二次枝晶间距为 116 μm，Laves 相的数量相对较少。 同时，由于低浇注温度的热控凝固工艺有效实现了凝固组织细化和缺陷控制，合金在 700 ℃条件下的抗拉强度提高了 7%，伸长率由 6%提高至 8%。

Advanced aeroengines and other high-temperature alloy components are constantly evolving towards more complex structures and thin-walled lightweight designs, potentially resulting in issues such as challenging casting, non-uniform microstructures, and solidification defects. These issues pose new challenges for precision casting techniques and process control in the manufacturing of such castings. In this regard, the filling ability, shrinkage, microstructure and mechanical properties of K4169 castings with thin walls and variable cross-sections were compared between conventional casting and thermally controlled solidification methods. The results show that under conventional casting, the filling percentage of the thin-walled part casting is only 26%, and porosity is found in the variable cross-section part. Thermally controlled solidification at a pouring temperature of 1 360 ℃ can increase the filling percentage by 226%, significantly reducing the shrinkage in the casting. A fine grain structure with an average grain size of 624 μm and secondary dendrite spacing of 116 μm is obtained during casting, where the amount of Laves phase is relatively small. Moreover, thermally controlled solidification at a low pouring temperature effectively achieves refinement of the solidification microstructure and defect control, the tensile strength of the alloy increases by 7%, and the elongation increases from 6% to 8% at 700 ℃.