热载荷下螺栓预紧力对非连续转子界面滑移特性影响  

Influence of bolt preload on slip characteristics at discontinuous rotor interfaces under thermal load

作　　者：洪志亮 李煜 何文博 丁水汀 Zhiliang HONG;Yu LI;Wenbo HE;Shuiting DING(College of Safety Science and Engineering,Civil Aviation University of China,Tianjin 300300,China)

机构地区：[1]中国民航大学安全科学与工程学院,天津300300

出　　处：《航空学报》2024年第24期203-216,共14页Acta Aeronautica et Astronautica Sinica

基　　金：国家自然科学基金(52276045);航空发动机及燃气轮机基础科学中心项目(P2022-B-I-003-001);国家重点研发计划(2022YFB4301001);中国民航大学研究生科研创新项目(2022SKYZ361)。

摘　　要：航空发动机转子非连续结构处多采用螺栓连接,其在热、力等多载荷作用下的动力学行为对整机振动具有重要影响,但相关研究鲜有开展。针对复杂热载荷与螺栓预紧力综合作用下连接界面滑移问题,首先建立基于单盘转子实验装置的有限元模型,进而设计实验,验证了该模型的有效性。然后以此建模方法,结合某型航空发动机涡轮盘与封严盘的连接特征,建立非连续转子双向热-固耦合模型,分析热载荷与非均匀螺栓预紧力对连接界面的影响。结果表明,周向非均匀的螺栓预紧力,在热载荷和离心力的共同作用下会导致连接界面出现周向非均匀变形,引起界面滑移,带来不平衡量。相较于受瞬时梯度热载荷作用,转子非连续结构处受均匀热载荷时上述不利影响更加显著。Bolted connections are commonly used at discontinuous structures of aero-engine rotors,whose dynamic behavior under various loads such as heat and force have a significant impact on the overall engine vibration.However,research in this area is scant.Focusing on the slip issue at the connection interface under the combined effect of complex thermal loads and bolt preload,we first establish a finite element model based on a single-disc rotor experimental setup,followed by experiments designed to verify the model validity.Then,using this modeling approach and combining the connection characteristics of a certain type of aero-engine turbine disc and sealing disc,we develop a bidirectional thermal-solid coupling model of the discontinuous rotor to analyze the effects of thermal loads and uneven bolt preload on the connection interface.The results indicate that the circumferentially uneven bolt preload,under the combined effects of thermal loads and centrifugal force,can lead to circumferentially uneven deformation at the connection interface,causing interface slip and imbalance.Compared to the effects of instantaneous gradient thermal loads,the adverse effects are more significant when the discontinuous structures of the rotor are subjected to uniform thermal loads.

关 键 词：螺栓预紧力 航空发动机转子 非连续结构 热-固耦合 界面滑移 

分 类 号：V235.13[航空宇航科学与技术—航空宇航推进理论与工程]