航空发动机压气机转静子高速摩擦机制研究进展  

Research Progress on High-speed Rub Mechanisms of Aero-engine Compressor Rotor-stator Systems

作　　者：裴会平 杨玉磊 姚利盼 程冰雪 PEI Huiping;YANG Yulei;YAO Lipan;CHENG Bingxue(State Key Laboratory of Tribology in Advanced Equipment,Tsinghua University,Beijing 100084,China;KeyLaboratory of Light-duty Gas-turbine,Institute of Engineering Thermophysics,Chinese Academy of Sciences,Beijing 100190,China;School of Mechanical Engineering,Nanjing University of Science and Technology,Nanjing 210094,China)

机构地区：[1]清华大学高端装备界面科学与技术全国重点实验室,北京100084 [2]中国科学院工程热物理研究所轻型动力实验室,北京100190 [3]南京理工大学机械工程学院,南京210094

出　　处：《中国表面工程》2024年第5期37-56,共20页China Surface Engineering

基　　金：清华大学自主科研计划(20224186005)。

摘　　要：航空发动机压气机转静子高速摩擦问题已有大量研究,但缺乏相关研究进展的系统介绍。从高速摩擦磨损和能量耗散机制出发,综述相关研究成果,对先进航空发动机安全设计具有重要意义。压气机转静子工作间隙小、线速度高、气流压力温度高,转静子径向碰磨不可避免,这种高速摩擦轻则造成涂层、叶片损伤,重则导致航空发动机“钛火”等严重事故。转静子高速摩擦受侵入速率、摩擦速度、摩擦深度等工况条件和叶片厚度、涂层硬度、材料热物性参数等摩擦配副自身特点的综合影响,摩擦磨损机制主要表现为黏着磨损、切削磨损或氧化磨损等,诸多因素中,侵入速率和摩擦速度的影响最为显著。对于高速摩擦热问题,温升预测是关键,而确定热流分配是难点,在早期基本假说基础上发展的不同热流分配计算方法,能够为摩擦温升预测提供理论依据,结合试验结果修正可提高计算可信度。高速摩擦热的产生会对摩擦磨损行为产生显著影响,而摩擦条件与摩擦机制的改变也会导致明显的能量耗散差别,进而影响摩擦热的生成和摩擦温升。首次从摩擦磨损与摩擦能量耗散角度进行系统综述,讨论引发“钛火”的摩擦热导致的温升计算方法,并提出采用流-热-固多场耦合方法开展研究的新观点。摩擦热的计算、转静子摩擦磨损机制的全面揭示和新型涂层体系的开发具有指导意义。The high-speed rub between the rotating and stationary parts of compressors plays a crucial role in the safe operation of aero engines.Extensive research has been reported on high-speed friction issues concerning compressor rotors and stators.Nevertheless,systematic reviews of relevant research progress have been lacking.This issue must be examined from the perspective of high-speed friction wear and energy-dissipation mechanisms so as to ensure the safe design of advanced aero engines.The operating conditions of the compressor rotor–stator systems are characterized by small radial clearances,high relative tangential velocities,high airflow pressures,and elevated temperatures,which inevitably result in radial rubbing.This high-speed rubbing can damage both the stator coatings and rotor blades,and in extreme cases,lead to serious safety incidents such as"titanium fires"in aero engines.This paper presents a systematic review of research findings pertaining to high-speed friction and wear in rotor–stator interactions,focusing on the mechanisms of friction-induced wear and the associated heat generation.On one hand,the high-speed friction between compressor rotors and stators is influenced by various operational parameters such as intrusion rate,sliding velocity,and contact depth.On the other hand,factors inherent to the rubbing surfaces,such as blade thickness,coating hardness,and material thermophysical properties,also play a crucial role in determining the rubbing behaviors and mechanisms.The predominant wear mechanisms include adhesive wear,abrasive wear,oxidative wear,and several wear maps have been established.Among the operational parameters,intrusion rate and rubbing velocity have the greatest influence.In addition to the typical stator coatings,several new coatings for both the rotor and the stator have been proposed,and corresponding friction and wear mechanisms have been investigated under laboratory conditions.Accurate prediction of the increase in temperature is critical for addressing the heat gener

关 键 词：航空发动机 压气机 高速摩擦 转静子 涂层 

分 类 号：TG156[金属学及工艺—热处理] TB114[金属学及工艺—金属学]