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:20030507:(1970-),(),,:1003-8728(2004)03-0329-03刘维伟,张定华,史耀耀,任军学,汪文虎(,710072):加工变形是影响薄壁零件数控加工效率精度和表面质量的关键性制约因素本文针对航空发动机薄壁叶片精密数控加工中的变形问题,在分析钛合金叶片结构和工艺特点基础上,提出了叶片的精确定位方案以及支撑叶片并控制弹性变形和残余应力变形的有效方法通过五坐标数控编程和加工试验对新方法进行了验证测试结果表明,采用新方法加工出的叶片满足设计性能要求,不但质量上优于传统制造工艺,而且制造成本显著降低周期缩短60%以上:航空发动机;薄壁叶片;数控加工;精确定位;变形控制:V232.4:AStudyonNe-tShapeNCMachingingTechnologyofThin-BaldeofAeroengineLIUWe-iwei,ZHANGDing-hua,SHIYao-yao,RENJun-xue,WANGWen-hu(KeyLaboratoryofMinistryofEducationforContemporaryDesignandIntegratedManufacturingTechnology,NorthwesternPolytechnicalUniversity,Xican710072)Abstract:Cuttingdeformationand/ordistortionarethekeyfactorsthatrestrictandlimitthecuttingefficiency,precisionandsurfacequalityofthin-parts.Tosolvetheeasy-to-be-distortedproblemsinaccurateorne-tshapeNCmachiningofthin-bladesofaero-engine,thestructuralandtechnicalfeaturesoftitanium-alloybladesareanalyzed.Thenwepresentanexactlylocatingmethodforblades,andaneffectivewaytosupportthebladeinordertocontroltheelasticdeformationand/orresidualstressdistortionduringandaftercuttingprocess.Five-axesNCprogrammingandblademachiningareperformed.Thetestresultprovedthattheexperimentalbladescompletelysatisfythedesignrequirements.Comparedwithtraditionalmachiningtechnique,thisnewmethodcanbringnotonlymuchhigherblademachiningprecision,butbettersurfacequality,andlowercost,andcanreducemachiningtimemorethan60%.Keywords:Aero-engine;Thin-blade;NCmachining;Deformationanddistortioncontrol30%,,:,;,;,;,,2090,,,,,,[1]:,,,,,233Vol.23No.320043MECHANICALSCIENCEANDTECHNOLOGYMarch2004111,:,340mm,120mm,0.45mm0.85mm,0.23~0.45mm,1/2001/40012,,,0.02mmTC4,,,,,,,2,,,/0,,2.1,[2],,,,,,))),[3]:(1),;(2),[3];(3)2.2,,,,/0:,,,2.3NC[4],,:,[7],TC4,,/0,2,,,,,,,,(2),,,,,33:,,,3.1OTa,3,P,QR1,OR1[6],B,R,R1,Re=R-33023R1(1-sinB)[6]ro=rp+rn+(R-r)(nsinB-fcosB)(1)Ta=ncosB+fsinB(2):roO,TaP3.2,DtDn,DnDt,D=|Dt|+|Dn|:Dt[18kfAB2,Dn[18R($H)2,$H=$B+$C,$B,$C,AB,,,,,,,,(R1),,0.01mm,12mm(),30b,,,8~12mm;,,3~5mm,,,4(1),()100,24;10,9,,(2),1,,,1(),0.02mm,,,,,?0.1mm,0.07mm,,5(1),(2),,(3),,,[][1],,.[J].,1999,31(4):84~87[2],,.[J].,1999,39(2):30~33[3],,.[J].,2001,19(3):376~380[4],.CAD/CAM[J].,2001,21(4):445~449[5],,.QFD[J].:,2001,37(8):38~42[6],.[M].:,2000[7],,.()[M].:,19983313: