航空发动机压气机转子叶尖间隙测量技术研究  

Research on Tip Clearance Measurement Technology of Aero-engine Compressor Rotor

作　　者：崔彬彬 李鹏飞 王娟 邹宇宁 CUI Bin-bin;LI Peng-fei;WANG Juan;无(AECC Shenyang Engine Research Institute,Shenyang 110015;AECC Shenyang Liming Aero-Engine Co.,Ltd.,Shenyang 110043)

机构地区：[1]中国航发沈阳发动机研究所,沈阳110015 [2]中国航发沈阳黎明航空发动机有限责任公司,沈阳110015

出　　处：《航空精密制造技术》2024年第6期9-12,共4页Aviation Precision Manufacturing Technology

摘　　要：为了解决航空发动机装配过程中利用塞尺检查压气机叶尖径向间隙不准确的问题,提出了一种新的测量计算方法,通过间接测量压气机机匣静子外环半径、转子叶尖半径,并综合考虑转、静子不同心度、核心机转子不同轴、压气机转、静子轴向位置的影响,间接计算获得设计状态下压气机转子叶尖径向间隙,其能更准确地反映装配状态下压气机叶尖径向间隙的分布,该方法可以保证综合测量精度不低于0.021mm。In order to solve the problem of inaccurate use of feeler gauges to check the radial clearance of compressor blade tips during the assembly process of aircraft engines.A measurement and calculation method is proposed.By indirectly measuring the outer ring radius of compressor casing stator and rotor blade tip radius,and taking into account the influence of different centeredness of rotor and stator,different axes of core engine rotor,axial position of compressor rotor and stator,indirect calculation can obtain the radial clearance of the compressor rotor blade tip in the design state,which could more accurately reflect the distribution of the radial clearance of the compressor blade tip in the assembly state.This method can ensure that the comprehensive measurement accuracy is not less than 0.021mm.

关 键 词：航空发动机 叶尖径向间隙 叶尖间隙数学模型 

分 类 号：V23[航空宇航科学与技术—航空宇航推进理论与工程] TP391.41[自动化与计算机技术—计算机应用技术]