跨声速压气机转子流场特性的数值研究

NumericalInvestigationonFlowFieldCharacteristicsofaTransonicCompressorRotor

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

Key words:  Transoniccompressor  Flowfieldcharacteristic  Numericalsimulation  Shockwave  Tipclearance

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。

Abstract:

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