航空发动机高压可调导向叶片角度卡滞故障及解决措施  

Fault and Solution of Angle Stuck of High Pressure Adjustable Guide Vane in Aero Engine

作　　者：黄猛 HUANG Meng(Second Military Representative Office of Military Representative Bureau of Air Force Equipment Department in Shenyang Area,Shenyang 110000)

机构地区：[1]空军装备部驻沈阳地区军事代表局驻沈阳地区第二军事代表室,沈阳110000

出　　处：《航空精密制造技术》2024年第2期23-26,共4页Aviation Precision Manufacturing Technology

摘　　要：某航空发动机在使用过程中出现可调导向叶片角度卡滞问题,造成压气机进气量与当前状态不匹配,稳定工作裕度降低,严重时造成发动机喘振。为解决该问题,采用问题树的分析方法,列出全部影响因素,逐一试验分析,确定问题的原因是作动筒出现磨损后可调导向叶片角度出现卡滞,使压气机工作状态严重偏离了设计工作状态,造成喘振。通过对作动筒结构改进、活塞杆采用毫克能表面处理工艺和优化作动筒封严工艺解决了该问题,改进措施经验证效果良好,为后续该类问题的分析解决提供了宝贵经验。The angle stuck of the adjustable guide blade occurs during the use of the type I aero engine,resulting in the mismatch between the compressor intake and the current state,the reduction of the stable operating margin,and the engine surge in serious cases.In order to solve the problem,the problem tree analysis method was used to list all the influencing factors,and the test analysis was carried out one by one.It was determined that the cause of the problem was the angle of the adjustable guide blade stuck after the actuator was worn,which made the working state of the compressor seriously deviated from the designed working state and caused surge.The problem was solved by improving the actuator structure,applying milligram energy surface treatment technology to the piston rod and optimizing the sealing technology of the actuator barrel.The improved measures have been proved to be effective,which provides valuable experience for the subsequent analysis and solution of this kind of problem.

关 键 词：导向器叶片 喘振 裕度 工艺 

分 类 号：V232.4[航空宇航科学与技术—航空宇航推进理论与工程]