端弯联合弯叶片对叶栅旋涡结构和气动性能的影响

推进技术 ›› 2016, Vol. 37 ›› Issue (11): 2072-2079.

端弯联合弯叶片对叶栅旋涡结构和气动性能的影响

丁骏¹,王松涛¹,刘勋²,王仲奇¹

哈尔滨工业大学发动机气体动力研究中心，黑龙江哈尔滨150001,哈尔滨工业大学发动机气体动力研究中心，黑龙江哈尔滨150001,中国船舶重工集团公司第七〇三研究所，黑龙江哈尔滨150078,哈尔滨工业大学发动机气体动力研究中心，黑龙江哈尔滨150001

发布日期:2021-08-15
作者简介:丁骏，男，博士，研究领域为压气机气动设计。
基金资助:
国家自然科学基金(51206035；51436002)；国家自然科学基金创新研究群体项目(51121004)。

EffectsofEnd-BowedBladeandDihedralBlade

EngineAerodynamicsResearchCentre，HarbinInstituteofTechnology，Harbin150001，China,EngineAerodynamicsResearchCentre，HarbinInstituteofTechnology，Harbin150001，China,No.703ResearchInstitute，ChinaShipbuildingIndustryCorporation，Harbin150078，China and EngineAerodynamicsResearchCentre，HarbinInstituteofTechnology，Harbin150001，China

Published:2021-08-15

摘要/Abstract

摘要： 为了研究弯叶片弯角、端弯弯高和端弯弯角三个参数对扩压叶栅流道内的旋涡结构和气动

关键词: 扩压叶栅；正交试验；弯叶片；端弯叶片

Abstract: Inordertostudytheeffectsandinteractionofthedihedralangle，end-bowedheightandangle

Key words: Compressorcascade；Orthogonalexperiment；Dihedralblade；End-bowedblade

丁骏,王松涛,刘勋,王仲奇. 端弯联合弯叶片对叶栅旋涡结构和气动性能的影响[J]. 推进技术, 2016, 37(11): 2072-2079.

DINGJun¹,WANGSong-tao¹,LIUXun²,WANGZhong-qi¹. EffectsofEnd-BowedBladeandDihedralBlade[J]. Journal of Propulsion Technology, 2016, 37(11): 2072-2079.

[1] WislerDC.CoreCompressorExitStageStudy.Vol1:BladingDesign[R].NASA-CR-135391,1977.第37卷第11期端弯联合弯叶片对叶栅旋涡结构和气动性能的影响2079
[2] WislerDC,KochCC,SmithLHJr.PreliminaryDesignStudyofAdvancedMultistageAxialFlowCoreCompressors[R].NASA-CR-135133,1995.
[3] LyesPA,GinderRB.Low-SpeedCompressorTestsofSweptandBowedBladeDesigns[R].ISABE99-7048.
[4] SimonJGallimore,JohnJBolger,NicholasACumpsty.TheUseofSweepandDihedralinMultistageAxialFlowCompressorBlading,PartI:UniversityResearchandMethodsDevelopment[J].JournalofTurbomachinery,2002,124(4):33-47.
[5] SimonJGallimore,JohnJBolger,NicholasACumpsty.TheUseofSweepandDihedralinMultistageAxialFlowCompressorBlading,PartII:LowandHigh-SpeedDesignsandTestVerification[J].JournalofTurbomachinery,2002,124(4):49-59.
[6] WoollattG,LippettD,IveyPC,etal.TheDesign,DevelopmentandEvaluationof3DAerofoilsforHighSpeedAxialCompressors,Part2:SimulationandComparisonwithExperiment[R].ASMEGT2005-68793.
[7] 季路成,李嘉宾,伊卫林.第三代三维叶片技术思路分析[J].工程热物理学报,2015,36(5):989-994.
[8] 陈绍文.不同折转角压气机叶栅中应用弯曲叶片的实验与数值研究[D].哈尔滨:哈尔滨工业大学,2007.
[9] 陈绍文,陈浮,王可立,等.采用弯叶片的不同折转角压气机叶栅流场气动性能[J].推进技术,2007,28(2):170-175.(CHENShao-wen,CHENFu,WANGKe-li,etal.AerodynamicPerformanceStudyofCurvedCompressorCascadeswithDifferentCamberAngles[J].JournalofPropulsionTechnology,2007,28(2):170-175.)
[10] 董平.航空发动机气冷涡轮叶片的气热耦合数值研究[D].哈尔滨:哈尔滨工业大学,2009.
[11] 陈绍文,兰云鹤,王春雪,等.基于转捩模型的吸附式压气机正弯叶片数值研究[J].推进技术,2014,35(9):1188-1193.(CHENShao-wen,LANYun-he,WANGChun-xue,etal.NumericalStudyofPositivelyCurvedBladeinAspiratedCompressorCascadeBasedonTransitionModel[J].JournalofPropulsionTechnology,2014,35(9):1188-1193.)
[12] 凌敬,杜鑫,王松涛,等.扩压叶栅最佳弯叶片生成线与进口马赫数之间的关系[J].推进技术,2014,35(10):1349-1355.(LINGJing,DUXin,WANGSong-tao,etal.RelationshipBetweenOptimumCurvedBladeGenerationLineandInletMachNumber[J].JournalofPropulsionTechnology,2014,35(10):1349-1355.)
[13] JeongJ,HussainF.OntheIdentificationofaVortex[J].JournalofFluidMechanics,1995,285(4):69-94.
[14] 蔡乐.低反动度高负荷扩压叶栅分离结构及其定常与非定常控制研究[D].哈尔滨:哈尔滨工业大学,2015.
[15] RobertsWB,SandercockDM.SecondaryFlowSpanwiseDeviationModelfortheStatorsofNASAMiddleCompressorStages[R].NASA-CR-173360,1984.
[16] RobertsWB,SerovyGK,SandercockDM.Modelingthe3-DFlowEffectsonDeviationAngleforAxialCompressorMiddleStages[J].JournalofEngineeringforGasTurbines&Power,1997,108(1):131-137.
[17] RobertsWB,SerovyGK,SandercockDM.DesignPointVariationofThree-DimensionalLossandDeviationforAxialCompressorMiddleStages[J].JournalofTurbomachinery,1988,110(4):426-433.(编辑:史亚红)