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1、第48卷第3期2016年6月南京航JournalofNanjingDOI：10．16356／j．1005—2615．2016．03．016空航天大學(xué)學(xué)報(bào)UniversityofAeronautics&Astronautics一種彈性支撐柔性轉(zhuǎn)子模態(tài)動(dòng)平衡方法陳曦廖明夫劉展翅李巖(西北工業(yè)大學(xué)動(dòng)力與能源學(xué)院，西安，710129)V01．48No．3Jun．2016摘要：針對(duì)目前模態(tài)平衡法難以高效平衡支承在彈性支承上的柔性轉(zhuǎn)子，提出一種考慮彈性支承影響的柔性轉(zhuǎn)子模態(tài)動(dòng)平衡方法，建立轉(zhuǎn)子的有限元模型，搭建轉(zhuǎn)子試驗(yàn)平臺(tái)
2、，計(jì)算并實(shí)測(cè)臨界轉(zhuǎn)速與振型，進(jìn)而借助動(dòng)平衡測(cè)試系統(tǒng)進(jìn)行模態(tài)動(dòng)平衡。結(jié)果表明：臨界轉(zhuǎn)速計(jì)算與實(shí)測(cè)的相對(duì)誤差僅為0．36％，一階計(jì)算振型與實(shí)測(cè)振型的模態(tài)置信度為0．9906。考慮彈性支撐的柔性轉(zhuǎn)子模態(tài)動(dòng)平衡方法合理，算法正確，在保證全正交平衡的前提下能夠減少試重的個(gè)數(shù)。左彈支與右剛支的計(jì)算支承剛度組合符合轉(zhuǎn)子結(jié)構(gòu)的實(shí)際情況，減振百分比CHl～CH3高達(dá)80％以上，CH4可達(dá)38％，總體減振效果明顯，具有一定的工程應(yīng)用前景，可為航空發(fā)動(dòng)機(jī)柔性轉(zhuǎn)子動(dòng)平衡試驗(yàn)提供技術(shù)參考。關(guān)鍵詞：彈性支承；模態(tài)動(dòng)平衡；振型；有限元；柔性
3、轉(zhuǎn)子中圖分類號(hào)：V231．1文獻(xiàn)標(biāo)志碼：A文章編號(hào)：1005—2615(2016)03—0402—08ModalBalancingMethodforFlexibleRotorswithElasticSupportsChenXi，LiaoMingfu，LiuZhanchi，LiYan(SchoolofPowerandEnergy，NorthwesternPolytechnicalUniversity，Xi’all，710129，China)Abstract：Anewmethodofmodalbalancingfo
4、rflexiblerotorsconsideringtheimpactofelasticsupportsisproposedsinceflexiblerotorssupportedonelasticsupportscannotbeefficientlybalancedusingthecurrentmodalbalancingmethod．AfiniteelementmodelofarotoriSestablishedandarotortestrigiSbuiltup．Aftercalculatingandmea
5、suringcriticalspeedsandvibrationmodes，modalbalancingisconductedthroughtherotortestingsystem．Resultssuggestthattherelativeerrorbetweenthecalculatedandmeasurederiticalspeedsisonly0．36％andthemodalassurancecriterionofthefirstcalculatedandmeasuredmodeshapesis0．99
6、06．Themethodofmodalbalancingforflexiblerotorscon—sideringelasticsupportsisreasonable，thealgorithmsarecorrectandthenumberoftrialmasscanbereducedunderthepremiseofensuringfullyorthogonalbalance．Acombinationofcalculatedsupportstiffness，i．e．，anelasticsupportatlef
7、tendandarigidsupportatrightend，isaccordantwiththeactualsituationofrotorstructureandthevibrationreductionpercentagesfromCHltoCH3reachmorethan80％andCH4upto38％．Astheoveralldampingeffectisobvious，themodalbalancingmethodconsideringelasticsupportshasaprospectineng
8、ineeringapplicationanditcanprovidetechnicalreferenceforbalancetestsofflexiblerotorsinaeroengines．Keywords：elasticsupport；modalbalancing；modeshape；finiteelement；flexiblerotor收稿El期：2015—07—23；修訂日期
