航空发动机弱刚性轴颈结构的预紧力加载损失问题研究  

Study on Preload Loss of Low-Rigidity Journal Structure in Aircraft Engine

作　　者：景晓明 刘振臣 庞健 JING Xiao-ming;LIU Zhen-chen;PANG Jian(AECC Hunan Aviation Powerplant Research Institute,Zhuzhou 412002,Hunan,China;Hunan Key Laboratory of Turbo Machinery on Small and Medium Aero-Engines,Zhuzhou 412002,Hunan,China)

机构地区：[1]中国航发湖南动力机械研究所,湖南株洲412002 [2]中小型航空发动机叶轮机械湖南省重点实验室,湖南株洲412002

出　　处：《机械研究与应用》2025年第1期92-95,99,共5页Mechanical Research & Application

摘　　要：圆弧端齿传扭+中心拉杆预紧是一种简单可靠的航空发动机转子连接结构,这种连接方式的一个明显特征是轴向预紧力最终作用在小尺寸、弱刚性轴颈结构的端面上,实际过程会出现预紧力加载损失较大的问题。针对上述问题,该文对弱刚性轴颈结构的工艺加载过程进行了受力分析,建立了预紧力加载损失模型,推导出实际加载预紧力公式并获得加载损失率。以某型端齿连接的转子为研究对象,通过数值仿真和试验测试的方法,对弱刚性轴颈结构的加载损失情况进行了分析和验证,结果表明,弱刚性轴颈结构的预紧力加载损失约为14%~18%,且与实际加载预紧力公式计算结果一致。建议在弱刚性轴颈结构的预紧力设计和试验阶段,充分考虑加载损失情况,并给出必要的加载补偿。Curvic couplings torque transmission with central pull rod preload is a simple and reliable rotor connection structure for aircraft engines.One obvious feature of this connection method is that the axial preload ultimately acts on the end face of small-sized,low-rigidity journal structure,therefore significant preload loss may occur during actual operation.In response to the above issue,force analysis was conducted on the preload process of low-rigidity journal structures,a preload loss model was established,and the actual preload formula was derived to directly obtain the preload loss rate.Taking a certain type of rotor with curvic coupling as the research object,the preload loss of low-rigidity journal structure was analyzed and verified through the numerical simulation and experimental tests.The results showed that the preload loss of the low-rigidity journal structure was about 14%to 18%,which was consistent with the calculated results from the formula of actual preload.It was recommended to fully consider the preload loss and provide necessary preload compensation during the preload design and test stage of low-rigidity journal structure.

关 键 词：预紧力 加载损失 弱刚性 轴颈 数值仿真 

分 类 号：V249.32[航空宇航科学与技术—飞行器设计]