Abstract: Atestrigwasbuilttostimulatethebearinglocatedinthebackstayofthehighpressureturbine.Inordertoidentifyandassesstheeffectsoftheinnerringassemblytechnologyonthevibrationoftherotor，anexperimentalinvestigationwasperformed.Arangeoffittolerancesandthetighteningtorquesofthelocknutwereusedtotestthedynamicbehavioroftherotor.Theexperimentalresultsrevealthatthepresenceofaninnerringinclearancefitandinsufficienttighteningtoqueintroduceshighnonlinearitytotherotor，thesupportofwhichre.spondswithrichfractionalharmoniccomponents.Withtheinnerringininterferencefit，therotorvibrationisal.mostindependentofthetighteningtoques.Withtheinnerringinclearancefit，aconsiderablylargetighteningtoqueiseffectiveinattenuatingthefractionalharmonicresponseoftherotorsupport.

Key words: Aero-engine；Turbine；Bearing；Innerring；Locknut；Tighteningtorque；Fittolerance

摘要： 试验研究航空发动机高压涡轮后支点轴承内环的装配工艺对转子支承系统振动特性的影响。改变转子轴承内环和内环衬套的配合公差与轴承内环锁紧螺母拧紧力矩，研究以上参数与转子支承系统振动响应的关系。结果表明:间隙配合和较小的锁紧螺母拧紧力矩给转子系统带来较强的非线性性，转子支承处出现丰富的分数倍频成分；过盈配合时转子振动对内环锁紧螺母拧紧力矩改变不敏感；间隙配合时，较大的锁紧螺母拧紧力矩可以抑制转子支承处的分数倍频成分。

关键词: 航空发动机；涡轮；轴承；内环；锁紧螺母；拧紧力矩；配合公差中图分类号:V231.9文献标识码:A文章编号:1001-4055(2015)12-1874-07DOI:10.13675/j.cnki.tjjs.2015.12.017