摘要
Abstract
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 veriifed by experimental comparison, design with reference to other rotor balancing technology and popularization value.关键词
航空发动机/低压涡轮/转子平衡/平衡工艺/稳定性试验Key words
aeroengine/low-pressure turbine/rotor balance/balance process/stability test分类
航空航天
