跨声速压气机转子流场特性的数值研究

推进技术 ›› 2015, Vol. 36 ›› Issue (12): 1795-1801.

跨声速压气机转子流场特性的数值研究

钟兢军¹,高宇¹,李晓东¹,姜雪红²

大连海事大学轮机工程学院，辽宁大连116026,大连海事大学轮机工程学院，辽宁大连116026,大连海事大学轮机工程学院，辽宁大连116026,大连交通大学外国语学院，辽宁大连116028

发布日期:2021-08-15
作者简介:钟兢军(1963—)，男，博士，教授，研究领域为叶轮机械气动热力学。

NumericalInvestigationonFlowFieldCharacteristicsofaTransonicCompressorRotor

MarineEngineeringCollege，DalianMaritimeUniversity，Dalian116026，China,MarineEngineeringCollege，DalianMaritimeUniversity，Dalian116026，China,MarineEngineeringCollege，DalianMaritimeUniversity，Dalian116026，China and SchoolofForeignLanguages，DalianJiaotongUniversity，Dalian116028，China

Published:2021-08-15

摘要/Abstract

摘要： 为研究跨声速压气机转子在设计转速下的内部流场特性，探索其流动机理，考察激波位置及成因，利用三维数值模拟方法对其进行了数值研究。结果表明，该跨声速压气机转子在设计转速下高效工作范围较宽，喘振裕度约为27.15%。近堵塞工况时，转子叶片前缘出现一道脱体的弓形激波，转子叶片流道内也存在一道正激波，激波位置随背压升高向叶片前缘移动；最高效率工况时，叶片前缘叶尖相对马赫数达到1.5。近失速工况时，流道内正激波消失。转子叶顶间隙处存在强烈的激波与附面层及间隙泄漏流的相互作用，该处熵值随背压升高而增大，高熵区随激波前移而向转子叶片前缘移动。

关键词: 跨声速压气机；流场特性；数值研究；激波；叶顶间隙中图分类号:V235.1文献标识码:A文章编号:1001-4055(2015)12-1795-07DOI:10.13675/j.cnki.tjjs.2015.12.006

Abstract: Inordertoinvestigatetheinnerflowfieldcharacteristicsofatransoniccompressorrotoratthedesignspeedandexploretheflowmechanism，shockwavelocationanddevelopmentunderthetransonicflowcondition，thethreedimensionalnumericalanalysisareused.Theresultshowsthatthetransoniccompressorro.torhasawideoperatingranges，thestallmarginis27.15%.Nearchokingcondition，abowshockwaveoccursontheleadingedgeoftherotorblade，andanormalshockwaveoccursintheflowpassage.Withthebackpres.sureincreasing，thelocationofshockwavemovesforwardtotheleadingedge.TherelativeMachnumberreachedby1.5atthetipbladeontheleadingedgeinpeakefficiencycondition.Nearstallcondition，thenormalshockwavedisappears.Thereexistsintenseinteractionbetweentheshockwave-boundarylayersandshockwave-tipleakageonthetipoftherotorblade.Theentropyincreasesatthatpositionwiththeincreaseofthebackpressure.Withtheshockwavemovingforward，theregionwithhighentropymovestowardstheleadingedgeoftheblade.

Key words: Transoniccompressor；Flowfieldcharacteristic；Numericalsimulation；Shockwave；Tipclearance

钟兢军,高宇,李晓东,姜雪红. 跨声速压气机转子流场特性的数值研究[J]. 推进技术, 2015, 36(12): 1795-1801.

ZHONGJing-jun¹,GAOYu¹,LIXiao-dong¹,JIANGXue-hong². NumericalInvestigationonFlowFieldCharacteristicsofaTransonicCompressorRotor[J]. Journal of Propulsion Technology, 2015, 36(12): 1795-1801.

参考文献

[1] RobertoBiollo,ErnestoBenini.RecentAdvancesinTransonicAxialCompressorAerodynamics[J].ProgressinAerospaceSciences,2013,56:1-18.
[2] RoehleI,GuevelALe,FradinC.3D-ShockVisualiza.tioninaTransonicCompressorRotor[J].OpticsLaserTechnology,1999,31:67-73.
[3] HilgenfeldL,CardamoneP,FottnerL.BoundaryLayerInvestigationsonaHighlyLoadedTransonicCompressorCascadewithShock/LaminarBoundaryLayerInterac.tions[J].ProceedingsoftheInstitutionofMechanicalEngineers,PartA:JournalofPowerandEnergy,2003,217(4):349-356.
[4] 刘波,曹志远,黄建,等.跨声速轴流压气机非轴对称端壁造型优化设计[J].推进技术,2012,33(5):689-694.(LIUBo,CAOZhi-yuan,HUANGJi.an,etal.DesignOptimizationforaTransonicCompres.sorwithImplementationofNon-AxisymmetricEndwallContouring[J].JournalofPropulsionTechnology,2012,33(5):689-694.)
[5] 杜文海,吴虎,孙娜.跨声速轴流压气机流动损失分析[J].推进技术,2008,29(3):339-343.(DUWen-hai,WUHu,SUNNa.AnalysisofFlowLossinTransonicAxialCompressors[J].JournalofPropulsionTechnology,2008,29(3):339-343.)
[6] 桂幸民,王同庆,于清,等.跨音压气机转子叶尖流场试验与分析[J].工程热物理学报,1998,19(5):553-558.
[7] 桂幸民,聂超群,王同庆,等.跨音压气机转子叶尖间隙复杂流动观测[J].工程热物理学报,2000,21(5):570-572.
[8] 王同庆,刘胤,吴怀宇.用PIV技术测量跨音压气机转子内流的激波结构[J].工程热物理学报,2002,23(3):297-300.
[9] 邓宝洋,桂幸民,袁巍,等.高负荷跨音压气机转子的间隙效应[J].北京航空航天大学学报,2002,28(4):387-390.
[10] 李泯江,祁祎,邓宝洋,等.高负荷跨音压气机转子ATS-3气动设计[J].航空动力学报,2002,17(2):183-187.
[11] YamadaK,FunazakiK.TheBehaviorofTipClearanceFlowatNear-StallConditioninaTransonicAxialCom.pressorRotor[R].ASMEGT-2007-27725.
[12] BergnerJ,KinzelM,SchifferH,etal.ShortLength-ScaleRotatingStallInceptioninaTransonicAxialCom.pressorExperimentalInvestigation[R].ASMEGT-2006-90209.
[13] HahC,BergnerJ,SchifferH.ShortLength-ScaleRo.tatingStallInceptioninaTransonicAxialCompressor-CriteriaandMechanisms[R].ASME2006-GT-90045.
[14] 吴艳辉,赵奎,田江涛,等.跨音压气机转子近失速工况叶尖非定常流动分析[J].工程热物理学报,2012,33(3):401-404.
[15] ReidL,MooreRD.DesignandOverallPerformanceofFourHighlyLoaded,High-SpeedInletStagesforanAd.vancedHigh-Pressure-RatioCoreCompressor[R].NASA-TP-1337,1978.
[16] DunhamJ.CFDValidationforPropulsionSystemCom.ponents[R].AgardAdvisoryReport355,1998.
[17] SuderKL,CelestinaML.ExperimentalandComputa.tionalInvestigationoftheTipClearanceFlowinaTran.sonicAxialCompressorRotor[J].JournalofTurbo-Ma.chinery,1996,118(2):218-229.
[18] 奉凡,郝增荣,顾春伟.间断Galerkin方法求解跨音压气机转子流场[J].工程热物理学报,2012,33(1):39-42.
[19] HoyingDA,TanCS,VoHD,etal.RoleofBladePassageFlowStructuresinAxialCompressorRotatingStallInception[J].JournalofTurbo-Machinery,1999,121(4):735-742.
[20] DaleEVanZante,AnthonyJStrazisar,JerryRWood,etal.RecommendationsforAchievingAccurateNumeri.calSimulationofTipClearanceFlowsinTransonicCom.pressorRotor[J].JournalofTurbo-Machinery,1999,122(4):733-742.
[21] KhalidSA,KhalsaAS,WaitzIA,etal.EndwallBlockageinAxialCompressors[J].JournalofTurbo-Machinery,1999,121(3):499-509.(编辑:史亚红)