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采用ANSYS软件模拟、射线检测和金相观察的方法研究了粉末注射成形增压涡轮“中空设计”对其结构可靠性及涡轮注射生坯充型冷却过程的影响。有限元分析表明,与实心涡轮相比,中空设计后叶片根部离心应力增加20%;模态分析表明,在气流冲击下的自振频率几乎不变;有限元法多相流模拟结果表明,中空涡轮注射生坯的中心高温区域减少,其可以有效缓解热致收缩引起的热裂和缩孔等缺陷的产生。通过X射线对相同工艺的空心涡轮和实心涡轮进行检测,发现在实心涡轮的心部存在裂纹,而空心涡轮质量完好。工业计算机断层扫描(CT)无损探伤和样件剖面分析也验证了模拟结果的可靠性,在涡轮中空孔内壁表层仅存在少量疏松、缩孔缺陷,没有发现裂纹型缺陷,满足了使用性能测试对涡轮成形质量的要求。
The effect of powder injection turbo-charged turbine “hollow design” on the structural reliability and the cooling process of the turbo injection green mold filling was studied by ANSYS software simulation, radiometric detection and metallographic observation. The finite element analysis shows that the centrifugal stress at the root of the hollow blade increases by 20% compared with that of the solid turbine. The modal analysis shows that the natural frequency under the impact of the air flow hardly changes. The simulation results of the multiphase flow show that the hollow The center of the turbine injection green body is reduced in the high temperature region, which can effectively alleviate the generation of defects such as thermal cracking and shrinkage caused by heat shrinkage. Through the X-ray detection of the same process hollow turbine and solid turbine, found in the heart of the solid turbine cracks, while the hollow turbine quality intact. Industrial computerized tomography (CT) non-destructive testing and sample section analysis also verify the reliability of the simulation results. There are only a few loose porosity and shrinkage defects in the inner surface of the hollow wall of the turbine, and no crack-type defects are found, which meets the requirements of service performance test Turbine forming quality requirements.