涡轮机械系统参数化三维叶片几何建模工具.pptx
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涡轮机械系统参数化三维叶片几何建模工具.pptx
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,Parametric3DBladeGeometryModelingToolforTurbomachinerySystems,KiranSiddappaji05/10/2012SchoolofAerospaceSystemsCommitteeChair:
Dr.MarkG.TurnerCommittee:
Dr.PaulD.OrkwisDr.ShaabanAbdallah,Overview,Motivation3DBGBProcessFlowchartInputParameterization3DBladeGeneratorGoverningEquationsBladesectionconstructionStreamwisemappingofbladesectionsSweepandLeanRadialstackingof3DbladesectionsCoordinatetransformation3DbladeloftingandCADconnectionExamplecasesConclusionandFutureWorkFlexibilityDemonstration,Motivation,Bladedesigndefinescomponentperformance.Iterative,hencerequiresquickerandrobustprocess.Aparametricapproachisdesired.DesigntoolwithlimitedCADinteraction.DesignFlexibilityandGeneralityaredesiredwithminimalinputmodifications.Mustbeapplicabletolargedesignspace.,Optiontobepartofanyautomationandoptimizationchain.,TheGENXEngine.1,3DBGB,3DBGB(3DimensionalBladeGeometryBuilder)isaparametricbladedesigntool.3Dbladesectionsarecreatedusingconformalmapping.Bladesectionscanberadiallystackedatanyspecifiedlocationtoobtaina3Dblademodel.Parametricsplineupdatemakesthegeometrymodificationprocessquicker.LimitedCADinteractiontoobtainnewerbladeshapes.,ProcessFlowchart,InputParameterization,Relativeflowanglesatleadingedgeandtrailingedgeoftheblade.Thicknesstochordratio,Axialchordvalues.Relativeinletmachnumber.Incidence,DeviationandSecondaryflowangles.LeadingandTrailingEdgecurves(x,r).Controlpointsdefiningleanandsweepperturbationsandanyotherquantity.Stackingoption.StreamlinecoordinatesfromanaxisymmetricrunlikeT-Axi2orsmoothconstructioncurves.,10stageHPCrotor1,10stageHPCrotor3,TIPVIEW,HUBVIEW,TIPVIEW,HUBVIEW,GoverningEquations,:
BladeSectionConstruction,Rotor1of10stageHPC,Non-dimensionalchordwisecoordinate:
uNon-dimensionalcoordinateperpendiculartou:
v,Inputs:
BlademetalanglesThicknesstochordratioMeridionalchord,*in*,out,=BlademetalangleatLeadingEdge=BlademetalangleatTrailingEdge,=RelativeflowangleatLeadingEdge,inout=RelativeflowangleatTrailingEdge=StaggerAngle,i=IncidenceAngle,ininin,=-*when*0,in,=*-when*0,inin=DeviationAngle,=*-(camber0)outout=out-*(camber0)out,CamberlineDefinitionandPlots,CamberLineplot,CamberAngleplot,Curvatureplot,Rotor1of10stageHPC,Staggeredandscaledairfoilcoordinates,Arrayubconsistsofubbotandubtop.Arrayvbconsistsofvbbotandvbtop.Thevaluesarestoredinacounterclockwisemannerstartingfromthetrailingedge.Nondimensionalleadingedgeis(0,0).Nondimensionaltrailingedgeis(1,0)forconvenience.Also,thkisthethicknessdefinitiongivenbyWennerstrom3.,(CoordinateRotation),(CoordinateScaling),(meridionalchord),(actualchord),Wennerstromthicknessdefinition3,Coefficientsathroughhcanbeobtainedwithproperboundaryconditions.AnellipticalLeadingEdgeandacircularTrailingedgeisused.Ellipticalleadingedgekeepstheflowattachedandlaminar4.,Varietyofairfoils,Capabilityofgeneratingdifferentairfoilshapesandhighlystaggeredairfoils.CurrentlycapableofNACA4digit,S809,circularandmixedcamber(default).,LeadingandTrailingEdgecurves,Definedby2Dcubicsplinecurvesinx,r.Cubicsplineisusedtofitthestreamlinecoordinatesxs,rswithmsasthesplineparameter.Intersectionoftheabove2splinecurvesproducesxLE,rLEandxTE,rTEoneachcorrespondingstreamline(constructioncurve).Usingthesepoints,msLE-theleadingedgemsvalueiscalculatedwhichiscrucialinstreamwisemappingofthebladesectionsasexplainedinthenextsection.,StreamwiseMappingoftheBladeSections,meridionaloffset:
Meridionaloffsetisnecessaryforpreciseconformationofthebladesectiononitscorrespondingstreamline.ThisisbecausethezeromsoneachstreamlineisdifferentfromthembLEoneachcorrespondingbladesection.,msLE=msvalueevaluatedatxLEonastreamline.mbLE=mbvalueattheLEoftheairfoil.,Similarly,StreamwiseCoordinateCalculation,x3D,r3Dand3Dcoordinatesarethuscalculated.,MappingoftheBladeSections,Mappingofthebladesectiononthecorrespondingstreamsurface.,Sweep,SpanwiseSweepPerturbation,PerturbationsaredefinedspanwiseusingfewcontrolpointsforacubicB-splinecurve.,CubicB-splineconstruction,5,Asimpleintersectionprocedureof2Dcurveandalinegivesthedesiredpointonthesmoothsplinecurve.,Lean,SpanwiseLeanPerturbation,PerturbationsaredefinedspanwiseusingfewcontrolpointsforacubicB-splinecurve.,Overview,Motivation3DBGBProcessFlowchartInputParameterization3DBladeGeneratorGoverningEquationsBladesectionConstructionStreamwiseMappingofbladesectionsSweepandLeanRadialStackingof3DbladesectionsCoordinateTransformation3DbladeloftingandCADconnectionExampleCasesConclusionandFutureWorkFlexibilityDemonstration,Radialstackingof3Dairfoils,Parametricradialstackingof3Dbladesectionswithoptions.Stackingisdefinedasapercentageofthechordwhichistransformedintotheaverage3Dcoordinate.Thestackvalueissubtractedfromthearrayof3Dcoordinates.StackingispossibleatLeadingEdge,TrailingEdge,%chordandatareacentroidofthebladesection.,CoordinateTransformation,Normalpracticeistoobtain3DbladecoordinatesintheCartesiansystem.TheengineaxisisassumedtobealongtheX-axiswhichmakesthexvaluesremainsameinbothcoordinatesystems.CylindricaltoCartesianSystem:
CylindricalCoordinateSystem,CartesianCoordinateSystem,3DBladeCADmodelandConnectingwithCAPRI,3DBladeloftedinUG.,ThesplineupdateofthebladeshapeisdoneparametricallybyconnectingtheblademodelwithCAPRIthroughascript.,CAPRIBlockDiagram.6,ExtrudedBlade,Fillets,UsingCAPRI,filletradiuscanbemodifiedeasily.,Overview,Motivation3DBGBProcessFlowchartInputParameterization3DBladeGeneratorGoverningEquationsBladesectionconstructionStreamwisemappingofbladesectionsSweepandLeanRadialstackingof3DbladesectionsCoordinatetransformation3DbladeloftingandCADconnectionExampleCasesConclusionandFutureWorkFlexibilityDemonstration,ExampleCases,10stageHighPressureCompressorFreeVortexDesignFullDefinitionDesign3stageBoosterforaTurbofanWindTurbineCentrifugalCompressor,10stageHighPressureCompressor,721bladerows;10stagesandanInletGuideVane.FreeVortexDesign.(Normalizedw.r.tLEtipradius)FullDefinitionDesign.(Normalizedw.r.tLEtipradius),-FreeVortexHPCDesign,SpanwiseconstantAngularMomentum.StraightLeadingandTrailingEdges;Flowanglesusedasblademetalangles.Rotor1androtor3bladesstackedattheirrespectiveleadingedges.,10stageHPCrotor1,10stageHPCrotor3,TIPVIEW,HUBVIEW,TIPVIEW,HUBVIEW,-FreeVortexHPCDesign,-FullDefinition10stageHPCDesign,SpanwisevariableAngularMomentum.Non-straightLeadingandTrailingEdges.Blademetalanglesandthicknesstochordratiodatainterpolatedfrom12pointsgivenintheNASAreport7to21points(#ofstreamlinesin3DBGBinput).First5rotorsstackedattheareacentroidofeachbladesectionandrestofthebladesarestackedatquarterchord.ThisdesignisbeingusedbyNASAtodefinetheEEEgeometryforanalysissincetheydonothavethegeometryfromGE.,-FullDefinition10stageHPCDesign,-FullDefinition10stageHPCDesign,3stageBoosterforaturbofan,Normalizedw.r.tLeadingEdgetipradius.Optimizedflowpath.,8,3DCFD,Rotor3oftheboosteroptimumwaschosenforanisolated3DCFDanalysisusingFINETM/Turbov8byNumeca9.GriddingisdoneusingAutoGrid510byimportingthe3Dbladesectionsandgivingahubandshrouddefinition.Thetipclearanceis0.15%ofrotortipradius.Thegridgeneratedismediumtypewith858149gridpoints.Inletboundaryconditions:
absolutetotalpressure,absolutetotaltemperature,spanwisedistributionofxatinletandcomingfromthepreviousbladerowExitboundaryconditions:
Staticpressure.,3DCFD,Point2R3EfficiencyT-Axi:
95.3%Un-leanedCFD:
93.2%LeanedCFD:
93.9%,3DDesign,UseofLean,B-splinecontrolpointsusedtoparameterizethelean.,Separationonun-leanedblade,Separationcleanedup,butstillnotoptimum,BladeStructuralFEA,FEAStructuralAnalysisofboosterrotor3bladeusingANSYSV12.011.Asimplescriptisusedtoperformtheanalysis.TetrahedralMeshwith22057nodesand94623elements.,ModalAnalysisofBoosterRotor3blade,AnimationforBladedeflectionatthe3rdmode,BoosterinCAD,bladerowUGpartfilesarecreatedin2steps.AssemblycreatedinUGfrom8bladerows,hubandcasing.,WindTurbine(Reverse-Engineered),Windturbinescanbetreatedasturbineswithoutthenozzle.Generalityof3DBGBisdemonstratedthroughbuildingthereverseengineeredGE1.5MWwindturbine.Capabilityofdesigningveryhighstaggeredblades.,12,BladeProfile13,FEAModalAnalysis,ANSYS12usedastheFEMsolverModalAnalysisDeterminesthefrequenciesandmodeshapeofthestructureduringfreevibration.185hexahedral8nodebrickelementusedMaterialused-Aluminum,Modeshapes(rpm=120.2Hz),13,Von-MisesStress,13,CentrifugalCompressor,Low-speedcentrifugalcompressor(LSCC)basedonaNASAdesign14wasdesigned.1862RPM,20blades.Normalizedwithleadingedgetipradius.Assumedpurelyaxialatinletandpurelyradialatexitwithconstantflowangleof55degreesspanwise.,14,CentrifugalCompressor,HubandTipflowpathfromthereport14werelinearlyinterpolatedintheradialdirectiontogenerateatotalof5constructionlines.Assumedconstantaxialvelocity,Vz.WheelSpeedatthetip,Ut=153m/s.Report14containedplotsofVz/Utratiosandanaveragevalueof0.4at50%pitchwasusedtocalculateVz.Vz=61.2m/s.Spanwiserelativeflowanglesatleadingedgearecalculatedasbelow:
CentrifugalCompressor,Bladesectionswerestackedatthetrailingedge.D
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- 涡轮 机械 系统 参数 三维 叶片 几何 建模 工具