涡扇发动机双悬臂低压模拟转子设计与动力学分析  

Design and Dynamic Analysis of Low Pressure Simulated Rotor with Double Cantilever for Turbofan Engine

作　　者：冯义 邓旺群 苏修文 胡廷勋 Feng Yi;Deng Wangqun;Su Xiuwen;Hu Tingxun(AECC Hunan Aviation Powerplant Research Institute,Zhuzhou 412002,China;Key Laboratory of Aero-engine Vibration Technology,Zhuzhou 412002,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]航空发动机振动技术重点实验室,湖南株洲412002

出　　处：《航空科学技术》2021年第12期127-134,共8页Aeronautical Science & Technology

基　　金：航空科学基金(2013ZB08001)。

摘　　要：某小型涡扇发动机的低压转子在国内首次采用0-4-0双悬臂结构,是一个超两阶弯曲临界转速工作的高速柔性转子,其结构和动力学设计的合理性必须通过试验验证,为降低研制风险、避免设计反复,在研制前期,很有必要针对低压模拟转子开展系统研究。本文遵循主体结构和动力学特性一致等原则,设计了一个低压模拟转子,建立了低压转子和低压模拟转子的有限元分析模型,采用Samcef/Rotor软件计算得到了两个转子的前三阶临界转速、振型和稳态不平衡响应并进行了对比分析。研究表明,低压模拟转子很好地反映了低压转子的实际情况,在低压模拟转子上取得的研究成果完全可以在低压转子上直接应用,为后续开展系统的试验研究奠定了基础,发展了双悬臂高速柔性转子的结构设计和动力学分析技术。The 0-4-0 double cantilever structure is adopted in the low-pressure rotor of a small turbofan engine for the first time at home. This is a high-speed flexible rotor which operates over the second order bending critical speed. The rationality of its structure and dynamics design must be verified by experiments. In order to reduce test risk and avoid design repetition,it is necessary to carry out systematic research on a low-pressure simulated rotor in the early stage of development. Based on the similar principle of structure and dynamics, a low-pressure simulated rotor is designed,and the finite element analysis models of two rotors are established. The first three critical speeds, vibration modes and steady-state unbalance responses of the two rotors are respectively calculated by using Samcef/Rotor software and analysis is finished by comparison. The research shows that the low-pressure simulated rotor reflects the actual situation of the low-pressure rotor very well. The research results of the low-pressure simulated rotor can be directly applied to the low-pressure rotor, which lays a foundation for subsequent experiment research, and develops the technologies of structure design and dynamics analysis of double cantilever high-speed flexible roto.

关 键 词：涡扇发动机 双悬臂高速柔性转子 结构设计 动力学分析 

分 类 号：V231.96[航空宇航科学与技术—航空宇航推进理论与工程]