摩擦热效应对航空发动机碰摩特性的影响分析  

Analysis of Influence of Friction Thermal Effect on Rub-impact Characteristics of Aircraft Engines

作　　者：张莹[1] 杨梓佟 孟祥鹏 ZHANG Ying;YANG Zi-tong;MENG Xiang-peng(School of Aeronautical Engineering,Civil Aviation University of China,Tianjin 300300,China)

机构地区：[1]中国民航大学航空工程学院,天津300300

出　　处：《计算机仿真》2025年第3期83-89,149,共8页Computer Simulation

基　　金：国家自然科学基金面上项目(52172360);在役公路安全设施技术状况评定方法研究和鉴定技术研发及标准规范(JTQG2022-3-13-1)。

摘　　要：航空发动机高压涡轮发生碰摩时产生的摩擦热效应会使碰摩点温度急剧升高,严重时会对叶片与机匣造成损伤,影响发动机正常运行。为研究摩擦热效应对碰摩特性的影响,基于有限元方法建立了高压涡轮叶片-机匣碰摩热-固耦合模型,结合发动机实际工作转速,对叶片与机匣发生多次碰摩后的的叶片温度、应力变化以及分布规律进行了分析。结果表明,碰摩点处的应力变化受碰摩程度影响,碰摩发生时,在接触应力作用下应力发生突变,其余时刻则受热应力影响;碰摩初始,叶根处应力最大,随着热应力积累导致叶尖应力变为最大;摩擦温度场以碰摩点为中心逐渐扩散,随着碰摩次数多增加升至较高温度;温度变化趋势与摩擦热流变化趋势以锯齿状升高;不同叶片以及不同节点处的温升规律均不相同。在实际工程问题中,需考虑碰摩时产生的摩擦热效应。The frictional heat effect generated when the high-pressure turbine of an aircraft engine collides can cause a sharp increase in the temperature of the collision point,and in severe cases,it can cause damage to the blades and casing,affecting the normal operation of the engine.In order to study the influence of the frictional thermal effect on the friction characteristics,a thermal-solid coupling model of high-pressure turbine blade-magazine friction is established based on the finite element method,and the blade temperature,stress change and distribution law of the blade and magazines are analyzed after several times of friction with the actual engine operating speed.The results indicate that the stress changes at the collision point are influenced by the degree of rub-impact.When rub-impact occurs,the stress undergoes a sudden change under the action of contact stress,while at other times it is affected by thermal stress;At the initial stage of rub-impact,the stress at the root of the blade is the highest,and as thermal stress accumulates,the stress at the tip of the blade becomes the highest;The friction temperature field gradually spreads around the rub-impact point and rises to a higher temperature with increasing rub-impact frequency;The temperature change trend and the frictional heat flux change trend increase in a zigzag pattern;The temperature rise patterns at different blades and nodes are not the same.In practical engineering problems,it is necessary to consider the frictional heat effect generated during the rub-impact.

关 键 词：航空发动机 高压涡轮 叶片-机匣 有限元 碰摩 摩擦热效应 

分 类 号：V235.1[航空宇航科学与技术—航空宇航推进理论与工程] TH16[机械工程—机械制造及自动化]