精密铸造0Cr17Ni4Cu3Nb不锈钢航空发动机零件  

Investigation and Optimization of Investment Casting 0Cr17Ni4Cu3Nb Stainless Steel Parts of Aero-Engines

作　　者：黄静 马原 王明杰 王晔[2] 吉泽升[2] Huang Jing;Ma Yuan;Wang Mingjie;Wang Ye;Ji Zesheng(AECC Shenyang Liming Aero-Engine Co.,Ltd.;School of Materials Science and Engineering,Harbin University of Science and Technology)

机构地区：[1]中国航发沈阳黎明航空发动机有限责任公司 [2]哈尔滨理工大学材料科学与工程学院

出　　处：《特种铸造及有色合金》2019年第2期159-162,共4页Special Casting & Nonferrous Alloys

摘　　要：基于数值模拟分析技术,采用正交试验和试验验证对熔模铸造ZG0Cr17Ni4Cu3Nb不锈钢航空发动机尾部搭接件中的缩孔进行了分析,研究了浇注温度、浇注速度和铸型温度对缩孔体积的影响。结果发现,浇注温度对铸件缩孔影响最大,其次是型壳温度。结合数值模拟对该铸件的浇注系统进行了优化。通过实际浇注试验对模拟结果进行验证,并试制出了合格的铸件。优化后的工艺方案:左右两侧的内浇口对称布置,浇注温度为1 560℃、浇注速度为320mm·s^(-1)、型壳温度为920℃。Based on the numerical simulation analysis,the shrinkage porosities in ZG0Cr17Ni4Cu3Nb alloy parts for tail lap part of aircraft engine,which was manufactured by investment casting,were investigated by the orthogonal experiment method and trial.The effects of the main process parameters,such as pouring temperature,casting speed and mold temperature,on probability of shrinkage volume were expounded.And the influence of various process parameters on shrinkage porosities was described.The results reveal that the pouring temperature has the largest effect and the second is the mold temperature.Combined with numerical simulation,the design of the gating system was also optimized.The reliability of the simulation results was verified through trial-production,and the qualified castings were produced sucessfully.The optimized process parameters are presented as follow:the symmetry arrangement of the inner gate on both sides,pouring temperature of 1 560℃,pouring rate of 320 mm·s^-1 and mold temperature of 920℃.

关 键 词：不锈钢 航空发动机 熔模铸造 缩孔 工艺优化 

分 类 号：TG142.7[一般工业技术—材料科学与工程] TG249.5[金属学及工艺—金属材料]