具有叶尖小翼的涡轮叶栅间隙流动的实验研究

推进技术 ›› 2015, Vol. 36 ›› Issue (12): 1825-1832.

具有叶尖小翼的涡轮叶栅间隙流动的实验研究

魏曼,钟兢军

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

发布日期:2021-08-15
作者简介:魏曼(1986—)，女，博士生，研究领域为叶轮机械气动热力学。
基金资助:
中央高校基本科研业务费专项资金资助(3132014319)；辽宁省高等学校创新团队支持计划资助(LT2015004)。

ExperimentalInvestigationonTipClearanceFlowofaTurbine

MarineEngineeringCollege，DalianMaritimeUniversity，Dalian116026，China and MarineEngineeringCollege，DalianMaritimeUniversity，Dalian116026，China

Published:2021-08-15

摘要/Abstract

摘要： 涡轮动叶叶顶间隙流动是引起动叶内部流动损失的重要因素之一，大约30%的流动损失是由间隙流动引起的。对高负荷涡轮叶栅在间隙高度1%叶高、0°冲角的条件下，加装不同宽度和安装位置的叶尖小翼进行了实验研究，结果表明，压力面小翼在一定程度上削弱了泄漏涡强度，0.3倍叶片当地厚度的压力面小翼效果最佳。吸力面小翼可使泄漏涡运动轨迹向相邻叶片的压力面侧偏移、泄漏涡强度减弱，间隙泄漏损失降低。随着吸力面叶尖小翼宽度的不断增加，叶尖小翼对泄漏流动的控制作用也不断增强，当宽度在1.2倍叶片当地厚度时，对泄漏流动控制效果最好，可使叶栅测量截面总损失与不加小翼的叶栅相比降低28%。组合小翼不如单纯的吸力面小翼效果好。

关键词: 涡轮叶栅；间隙泄漏流动；叶尖小翼；实验研究中图分类号:V235.1文献标识码:A文章编号:1001-4055(2015)12-1825-08DOI:10.13675/j.cnki.tjjs.2015.12.010

Abstract: Tipleakageflowisoneofthemostinfluentialfeaturesoftheflowthroughturbinerotor，whichisresponsibleforasmuchas30%ofthetotalaerodynamiclosses.Adetailedexperimentalstudyhasbeencarriedouttoinvestigatetheeffectofbladetipwingletwithdifferentinstallationpositionsanddifferentwidthsontheper.formanceofaturbinecascade，under1%bladeheighttipclearances，0°angleofattack.Experimentalresultsshowthat，forthecaseswithpressure-sidewinglet，thestrengthoftipleakagevortexcanbereducedandtheop.timalwingletwidthis0.3timesofthelocalbladethickness.Forthecaseswithsuction-sidewinglet，thetipleak.agevortextrajectoryshiftstowardthepressuresurfaceoftheadjacentblade.Moreover，thestrengthoftipleak.agevortexandthetipleakagelossarereduced.Asthewingletwidthincreases，theeffectsofthesuction-sidewingletonleakageflowareenhanced.Theoptimalwingletwidthisabout1.2timesofthelocalbladethicknessandthetotalpressurelossofthecascadesmeasuringsectionisreducedbyabout28%whencomparedwiththebaselinetipblade.Theinfluenceofcombinedwingletcaseisnotaseffectiveassuction-sidewingletcase.

Key words: Turbinecascade；Tipleakageflow；Tipwinglet；Experimentalinvestigation

魏曼,钟兢军. 具有叶尖小翼的涡轮叶栅间隙流动的实验研究[J]. 推进技术, 2015, 36(12): 1825-1832.

WEIMan,ZHONGJing-jun. ExperimentalInvestigationonTipClearanceFlowofaTurbine[J]. Journal of Propulsion Technology, 2015, 36(12): 1825-1832.

参考文献

[1] ShimPeiM,HoshioT.NumericalCalculationofFlowforCascadewithTipClearance[R].ASME94-GT-361.
[2] BindonJP,MorphisG.TheDevelopmentofAxialTur.bineLeakageLossforTwoProfiledTipgeometriesUsingLinearCascadeData[J].JournalofTurbomachinery,1992,114(1):198-203.
[3] DentonJD.LossMechanismsinTurbomachines[J].JournalofTurbomachinery,1993,115(4):621-656.
[4] CamciC,DeyD,KavurmaciogluL.TipLeakageFlowsnearPartialSquealerRimsinanAxialFlowTurbineStage[R].ASMEGT2003-38979.
[5] 江永泉.飞机翼梢小翼设计[M].北京:航空工业出版社,2009.
[6] 贾瑞博.风力机叶尖加小翼动力放大的数值模拟研究[D].呼和浩特:内蒙古工业大学,2005.
[7] 崔承根,施能继.叶梢带端板螺旋桨的性能研究[J].华中理工大学学报,1991,19(3):117-120.
[8] 韩少冰.叶尖小翼控制压气机叶顶间隙流动的研究[D].大连:大连海事大学,2013.
[9] 韩少冰,钟兢军.变冲角下吸力面小翼对压气机叶栅气动性能的影响[J].推进技术,2012,33(3):384-390.(HANShao-bing,ZHONGJing-jun.EffectsofSuction-SideWingletonAerodynamicPerformanceofCompressorCascadeatDifferentIncidences[J].Jour.nalofPropulsionTechnology,2012,33(3):384-390.)
[10] 钟兢军,严红明,韩吉昂,等.涡轮或汽轮机动叶叶尖小翼[P].中国专利:ZL200810010516.9,2010.
[11] PatelKV.ResearchonaHighWorkAxialGasGenera.torTurbine[R].ASAE800618,1980.
[12] BoothTC,DodgePR,HepworthHK.Rotor-TipLeakage:PartI-BasicMethodology[J].JournalofEngi.neeringforGasTurbinesandPower,1982,104(1):154-161.
[13] DeyD,CamciC.TipDesensitizationofanAxialTur.bineRotorUsingTipPlatformExtensions[R].VKILec.tureSeries,2004-02.
[14] JamesA.Tallman.AComputationalStudyofTipDe.sensitizationinAxialFlowTurbines.Part1:BaselineTurbineComputationsandComparisonswithMeasure.ment[R].ASMEGT2004-53918.
[15] TallmanJamesA.AComputationalStudyofTipDesen.sitizationinAxialFlowTurbines.Part2:TurbineRotorSimulationswithModifiedTipShapes[R].ASMEGT2004-53919.
[16] 王生武,石秀华.涡轮叶尖压力边小翼肋条对泄漏流场的数值模拟[J].计算机测量与控制,2009,17(8):1527-1534.
[17] 蔡晋.带小翼肋条的涡轮叶尖泄漏流场的数值模拟[J].动力工程学报,2010,30(12):919-925.
[18] 王大磊,邵伏永,郭昊雁,等.翼梢小翼对涡轮间隙泄漏流动影响的数值研究[J].推进技术,2014,35(3):341-346.(WANGDa-lei,SHAOFu-yong,GUOHao-yan,etal.StudyofTipWingletsonleakageFlowinaTransonicTurbineStage[J].JournalofPropulsionTechnology,2014,35(3):341-346.)
[19] ThomasBehr.ControlofRotorTipLeakageandSecond.aryFlowbyCasingAirInjectioninUnshroudedAxialTurbines[D].Swiss:SwissFederalInstituteofTechnolo.gyZurich,2007.(编辑:张荣莉)