航空发动机带止口转子结构装配工艺方法研究
Research on the Assembly Process Method of Aero-Engine Rotor Structure with Stopcock
张伟刚1
作者信息
- 1. 中国航发哈尔滨东安发动机有限公司,黑龙江 哈尔滨 150066
- 折叠
摘要
为进一步探究航空发动机带止口转子结构装配工艺的可能优化路径,以涡扇航空发动机低压涡轮轴-盘的带止口结构为研究对象,探究装配工艺中的螺栓紧固策略与带止口过盈量两项主要内容的影响,以此确定采用三角紧固方法对涡扇航空发动机低压涡轮轴-盘的带止口结构进行装配,并将装配过程中的带止口结构过盈量设置为0.1 mm.从现场实验测试结果来看,该装配工艺方法各项主要指标均显著优于传统装配工艺,有望在后续装配中逐步得到应用.
Abstract
In order to further investigate the possible optimisation path of the assembly process of aero-engine rotor structure with stop-port,taking the low-pressure turbine shaft-disc of turbofan aero-engine as the object of research,we investigate the influence of the two main contents of the bolt fastening strategy and the excess of the stop-port in the assembly process,so as to determine the use of the triangular fastening method for the low-pressure turbine shaft-disc of turbofan aero-engine,and set the excess of the band-port in the assembly process to 0.0％,and set the excess of the band-port in the assembly process to 0.0％.The excess of the belt stop structure in the assembly process is set to 0.1 mm.From the results of field experiments,all the main indexes of this assembly process are significantly better than the traditional assembly process,and it is expected to be gradually applied in the subsequent assembly.
关键词
航空发动机/带止口/转子结构/装配工艺Key words
aero-engine/with stop/rotor structure/assembly process引用本文复制引用
出版年
2024
NETL
NSTL
万方数据