简介：Aprocessfornumericalanalysisofradialcirculationdistributionofpropellerbladeisproposedandpresented.Itisbasedontheresultsofnumericalsimulationofthevelocityfieldaroundpropellerbladesandinthewake.Thewell-knowntraditionalmethodusingtangentialvelocitydatainthewakeandapplyingStockes'stheoremwasalsoexaminedintheinvestigation.Theresultsfromtwoapproachesarecomparedwitheachother.Itisfoundthatifthetraditionalwayisutilized,inmanycasesanunexpected'hump'appearsinthecirculationdistributionatcertainouterradius.Theauthorscalculatedthecirculationsdirectlyaroundbladesections,anditisreferredasdirectmethod.Theunexpectedhumpofthecirculationdistributiondisappearsintheresultsofdirectmethod.Thisarticlealsodiscussesthereasonsoftheappearanceoftheunexpectedhumpintraditionalapproach.Thedirectmethodisproposedtohaveapotentialinanalyzingorverifyingtheradialroaddistributionfordesignedpropellerandthenumericalanalysisinsteadofexperimentalvalidationforcirculationdistributioncanbeasatoolinthepropellerdesignprocess.

简介：Geometricparametersoftheturbinebladeareclassifiedaccordingtotheirdestinedfunctions,andthemathematicaldefinitionofthoseparametersinthesectioncurveisintroducedindetail.Somepartsofthesectioncurveshapecanbeadjustedfreely,offeringmoreflexibilitytodesigners.

简介：Anexperimetalinvestigationwascarriedoutontheeffectofbladechordwiseleanonthelosseinhighlyloadedrectangularturbinecascades,Datailedmeasurementsinclude10traversesfromupstreamtodownstreamofthecascadeswithfive-holesphericalprobes.ComparedwiththeexperimentaldataofthecoventionalStraightandpitchwiseleanbladesunderthesameconditions,itisshownthattheeffectofchordwiseleanonthedevelopmentofthecascadelossesissimilartothatofpitchwiselean.However,thechordwiseleanproducessmallerstreamwiseadversepressuregradientsnearbothendwallsandasmallerspanwisenegativeonestartingfromtheactuteanglesideinthefirstpartofthepassagesinchordwiseleancascade,therebythesaddlepointseparationsandintensitiesofthepassagevorticesareweakenedandthesecondaryvortelossesarecutdownnotably.

简介：飞机引擎片/盒子抑制分析上的试验性、数字的调查被介绍。片外面抑制能力分析是在新飞机引擎设计的必要的步，但是抑制测试是费时间的并且招致重要费用；因此，开发一个短时期、便宜的数字方法被保证。用明确的非线性的动态有限元素分析软件，现在的学习数字地为在测试设备的高速度的纺纱上被执行的模仿的片抑制测试调查了高速度的影响过程。很多模拟与不同网孔尺寸和接触惩罚因素和磨擦系数的不同价值用有限元素模型被进行。在试验性、数字的结果之间的详细比较表明网孔尺寸和磨擦系数在生产的结果上有可观的影响。一个更好的网孔将预言案例的更低的抑制能力，这被显示出，它接近测试数据。磨擦系数的更大的价值也预言更低的抑制能力。然而，如果避免假穿入足够大，接触惩罚因素在模拟结果上有小效果。

简介：在这篇论文，表演和传统的类型的声学的噪音，微多片扇子试验性地并且数字地被调查，到为居民情形优化扇子的说明。声学的噪音水平减少，但是效率随impeller的片数字的增加稍微败坏。而且，声学的噪音随在impeller插头和涡囊舌头之间的距离的增加减少，在随输入的增加和扇子效率的恶化伴随。

简介：ThispaperdetailstheresultsofajointprojectbetweenRolls-RoyceDeutschland(RRD)andtheNorthwesternPolytechnicalUniversityofChina(NWPU).Theobjectiveoftheprojectwasthedeterminationoftheinfluenceoftabulatorsinturbinebladecoolingpassagesonfilmholedischargecoefficients(Cdcoefficients).Alarge-scaleplexiglasmodelwasusedbytheNWPUtomeasuretheturbulatorinfluenceonCdcoefficientsforawiderangeofdifferentgeometricalparameters,Reynoldsnumbersandcoolingflowofftakeratios.RRDspecifiedthecomprehensivetestmatrixandanalysedthetestdata.TheCFDcodeFLUENTwasusedbyRRDfornumericalsimulationofthetestcaseswiththemainobjectivetosupporttheinterpretationofobservedtrends.Both,experimentalandnumericalresultswillbepresentedinthispaperforaselectionoftestconfigurations.

简介：参考价格：约40万元KEF《极而峰》推出了一款非常具有创新意义的扬声器——CONCEPTBLADE，它是KEF费时三年进行详尽无遗的测试、专家级分析和复杂试验的结晶．所有组件都彻底重新设计．其中涉及的材料工程技术极其复杂和精密，而所蕴涵的工程设计理念却如同其流线型外形一样简约。

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简介：ByadoptingthesolidmodelingsoftwareSoldEdgeandtheenmeshmentsoftwareSRIFCastasthepre-processingplatform,aNibasedalloyturbinebladewasthree-dimensionallymodeledandautomaticallyenmeshed.Asoftwarecodefornumericalsimulationoffluidflowandheattransferwasdeveloped.TheXuecriterionandNiyamacriterionwereusedtopredictthepositionoftheshrinkagedefectsoccurringinthesolidificationprocessesoftheturbineblade.TheresultsshowedthatbothXueandNiyamacriteriacouldpreciselypredicttheshrinkagedefectsintheNibasedalloyturbineblade.Thisindicatesthatnumericalsimulationisasignificanttoolinimprovingcastingquality.

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简介：不知道在看文章的您，是否有留意香港的流行乐坛呢？是否还记得当年谭张争霸、四大天王的盛况？是否有几首粤语流行曲到现在还朗朗上口？当然，不得不承认，

简介：Thispaperpresentsastudyofthemovementandthehydrodynamicperformanceofanewtide-poweredhydraulicturbinethroughnumericalsimulations.Bymeansofthemovingmeshmethod,theopen-closedsequencesofthebladesandthemovementoftherotorsareobtainedandtheangularvelocityandtheaverageenergyutilizationcoefficientunderdifferenttipspeedratiosarealsoobtained.Moreover,theoptimumtipspeedratioisidentifiedbyintegratingtheoutputpowerandtheenergyutilizationcoefficientofthehydraulicturbinewithdifferenttipspeedratios,providingdatasupportfortheprototypedesignofthehydraulicturbine.

简介：Analgorithmforcomputingthe3-Doscillatingflowfieldofthebaldepassageunderthetorsionalvibrationoftherotorisappliedtoanalyzethestabilityinturbomachines.TheinducedflowfieldrespondingtobladevibrationiscomputedbyOscillatingFluidMechanicsMethodandparametricPolynomialMethod.Aftergettingthesolutionoftheunsteadyflowfield,theworkdonebytheunsteayaerodynamicforceactingonthebladecanbeobtained.Thenegativeorpositiveworkisthecriterionoftheaeroelasticstability.Numericalresultsindicatethatthereareinstabilitiesofthetorsionalvibrationinsomefrequencybands.

简介：现在的纸为与快速的3D片和格子生成器(RAPID3DGRID)相结合的turbomachinery的空气动力学的设计描述优化方法论，一个N.S解答者，一个片parameterization方法(BPM)，一个基于坡度的analyseparameterization方法(GPAM)，有激增的一个反应表面方法(RSM)算法和一个简单坡度方法。由片parameterization方法的使用，一个接近音速的压缩机转子能被一套多项式表示，然后它使我们能转变表示坐标的片数据到表示参数然后减少参数的数字。与改变任何一个参数，我们能获得几组样品。这里，仅仅十个参数被认为寻找一个优化压缩机转子。由于优化，断热的效率被1.73%增加。

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简介：Infive-axismachining,toolorientationaboveabladestreamsurfacemayleadtotoolcollisionandadecreaseinworkpiecerigidity.Hence,collisionlesstoolorientationsmoothing(TOS)becomesanimportantissue.Onthebasisofaconstantscallopheighttoolpath,thetriangularfacetsinthefaces,verticesformatareconstructedfromcuttercontact(CC)usingtheVoronoiincrementalalgorithm.Thecutterlocation(CL)pointscandidatesetisrepresentedbyanobliqueellipticconewhosevertexliesatCCusingNURBSenvelope.WhethertheCLpointisaboveitsCCisjudgedbythedotproductbetweenthenormalvectorandthepointontriangulationnearesttotheCLpoint.ThecurvaturesatCCareobtainedbyfittingamovingleastsquare(MLS)quadraticpatchtothelocalneighborhoodofavertexandcalculatingeigenvectorsandeigenvaluesoftheHessianmatrix.TriangularsurfaceelasticenergyisemployedastheweightinselectionfromtheNURBSenvelope.ThecollisionisjudgedbyNURBSsurfaceintersection.TOScanthenbeexpressedbyselectingaCLpointforeachCCpointandconvertedintoanumericalcontrol(NC)codeautomaticallyaccordingtothepostprocessortypeofthemachinecenter.Theproposedmethodisverifiedbyfinishingofacryogenicturboexpanderimpellerofairseparationequipment.

简介：Vibrationfatigueisthemainfailuremodeofcompressorblade.Evaluatingthevibrationstressofbladethatleadstocrackingisveryusefulforanalysisofvibrationfatigue.Inthispaper,fatiguestressestimationmethodsbyquantitativefractographywerestudiedthroughexperimentalbladeandin-servicefirst-stagecompressorbladeinordertoevaluatetheinitiationvibrationstressofin-serviceblade.Theanalysisprocessofinitiationvibrationstresswasestablished.Theevaluatingresultofvibrationstressofin-servicebladesubjectedtocentrifugalforceandbendingvibrationstressagreeswithaeroenginetestresult.Itisshownthattheevaluationmethodcannotonlyevaluatetheequivalentfatiguestressesofdifferentcrackdepthsbutalsoyieldtheinitiationequivalentfatiguestress.

简介：这份报纸论述对流动结构和热的隧道几何学的影响的学习转，并且也，他们一个光线的冷却段落的所有墙上的关联煤气的汽轮机片当模特儿。调查在隧道集中于热转移和空气动力学的大小，它是在飞机引擎使用的配置的一个精确代表。为热转移系数和在内部冷却段落的设计使用的压力落下的关联经常从简化模型被开发。一个角落切，对真实引擎段落没有完美的矩形的生气的节的笔记重要，但是包括，肋骨与切半径和特殊取向。因此，这个工作为有很现实主义的特征的光线的冷却几何学的一个模型提供详细液体流动和热转移数据。

简介：有比100mm小的一条直径的微型涡轮泵在许多地里被采用；汽车散热器泵，室帮助泵，为电的设备的冷却的泵，洗衣机泵等等。进一步，对微型涡轮泵的需要将为电的机器随它的申请的增加变得更大。微型涡轮泵设计由于限制是尽可能简单的做精确制造，是合乎需要的。但是因为为这些小型的液体机械的内部流动条件没被澄清，常规理论不为小型的泵是传导性的，为微型涡轮泵的设计方法没被建立。有不同插头角度的转子的三种类型为一个实验和数字分析作好准备。表演测试与这些转子被进行以便在性能和微型涡轮泵的内部流动状况上调查片插头角度的效果。它从到更大的流动的那头微型涡轮泵增加和最大的效率流动率移动根据片插头角度的增加评估的试验性的结果被澄清，然而，最大的效率随它的增加减少。在现在的纸，微型涡轮泵的表演被显示出，内部流动条件与实验和数字流动分析的结果被澄清。而且，表演上的片插头角度的效果被调查，有为微型涡轮泵的简单结构的高效设计将被考虑。

简介：Icing(oriceaccretion)isaphenomenoninwhichsuper-cooledwaterdropletsimpingeandaccreteonabody.Itiswellknownthaticeaccretiononbladesandvanesleadstoperformancedegradationandhascausedsevereaccidents.Althoughvariousanti-icinganddeicingsystemshavebeendeveloped,suchaccidentsstilloccur.Therefore,itisimportanttoclarifythephenomenonoficeaccretiononanaircraftandinajetengine.However,flighttestsforiceaccretionareveryexpensive,andinthewindtunnelitisdifficulttoreproduceallclimateconditionswhereiceaccretioncanoccur.Therefore,itisexpectedthatcomputationalfluiddynamics(CFD),whichcanestimateiceaccretioninvariousclimateconditions,willbeausefulwaytopredictandunderstandtheiceaccretionphenomenon.Ontheotherhand,althoughtheicingcausedbysuper-cooledlargedroplets(SLD)isverydangerous,thenumericalmethodhasnotbeenestablishedyet.ThisiswhySLDicingischaracterizedbysplashandbouncephenomenaofdropletsandtheyareverycomplexinnature.Inthepresentstudy,wedevelopaniceaccretioncodeconsideringthesplashandbouncephenomenatopredictSLDicing,andthecodeisappliedtoafanrotorblade.ThenumericalresultswithandwithouttheSLDicingmodelarecompared.Throughthisstudy,theinfluenceoftheSLDicingmodelisnumericallyclarified.