摘要
航空发动机低压涡轮转子具有结构紧凑、重心靠近轴承支撑端、装配精度要求高等特点,给转子平衡带来了极大挑战。在分析该转子结构特点的基础上,提出并详细论述了低压涡轮转子带支点轴承与不带支点轴承两种平衡方案,进而对两种方案工装设计的关键因素及方案实施的优缺点进行分析,总结了轴套类和框架类平衡工装的设计准则,并通过试验对比验证了两种方案的稳定性,对其他转子平衡工艺方案设计具有参考及推广价值。
The low-pressure turbine rotor of aeroengine has the characteristics of compact structure, center near end bearing and high assembly accuracy, brings great challenge to the rotor balance. In this paper, on the basis of analyzing the structural characteristics of the rotor, put forward and discussed in detail with pivot bearings with low pressure turbine rotor, without pivot bearing two equilibrium solution. And then analyzed the key factors and the advantages and disadvantages of two kinds of scheme design. Summarized the shaft sleeve and framework class balance tooling design criterion, and the stability of the two schemes was verified by experimental comparison, design with reference to other rotor balancing technology and popularization value.
出处
《航空科学技术》
2016年第2期25-28,共4页
Aeronautical Science & Technology
