資源描述：
《軸流壓氣機(jī)特性計(jì)算及激波模型研究.pdf》由會(huì)員上傳分享，免費(fèi)在線閱讀，更多相關(guān)內(nèi)容在行業(yè)資料-天天文庫(kù)。
1、第43卷第2期2017年4月航空發(fā)動(dòng)機(jī)AeroengineV01．43No．2Apr．2017軸流壓氣機(jī)特性計(jì)算及激波模型研究蔣筑宇1，范召林1，劉波2(1．中國(guó)空氣動(dòng)力研究與發(fā)展中心，四川綿陽(yáng)621000；2．西北工業(yè)大學(xué)動(dòng)力與能源學(xué)院，西安710072)摘要：為快速準(zhǔn)確預(yù)估軸流壓氣機(jī)特性和激波損失，基于軸流壓氣機(jī)S2流面流線曲率法，分別采用正激波模型和改進(jìn)的雙激波模型，對(duì)某型2級(jí)跨聲速風(fēng)扇特性進(jìn)行數(shù)值模擬計(jì)算，得到了100％設(shè)計(jì)轉(zhuǎn)速近設(shè)計(jì)點(diǎn)與99．76％設(shè)計(jì)轉(zhuǎn)速近堵塞點(diǎn)的總體性能和氣動(dòng)參數(shù)，以及95％、100
2、％和110％設(shè)計(jì)轉(zhuǎn)速的特性曲線。通過(guò)將計(jì)算結(jié)果與試驗(yàn)數(shù)據(jù)進(jìn)行對(duì)比，分析研究了各激波損失模型在激波損失預(yù)估和風(fēng)扇／壓氣機(jī)特性計(jì)算方面的差異。分析結(jié)果表明：在跨聲速風(fēng)扇／壓氣機(jī)近設(shè)計(jì)點(diǎn)激波損失和特性參數(shù)的計(jì)算中，正激波模型損失徑向分布計(jì)算結(jié)果接近試驗(yàn)值，總壓比和總效率計(jì)算值分別較試驗(yàn)值約低1．96％和2．54％，模型能夠滿足工程需要。而在近堵塞點(diǎn)，改進(jìn)的雙激波模型總損失計(jì)算值更接近試驗(yàn)值，總壓比計(jì)算值和試驗(yàn)值很吻合，總效率計(jì)算值比試驗(yàn)值約高7．28％。改進(jìn)雙激波模型的不同轉(zhuǎn)速線效率特性曲線也明顯更接近試驗(yàn)值，模型能夠
3、較準(zhǔn)確地預(yù)測(cè)遠(yuǎn)離設(shè)計(jì)點(diǎn)激波損失和特性參數(shù)。關(guān)鍵詞：軸流壓氣機(jī)；流線曲率法；激波模型；損失預(yù)估；特性計(jì)算中圖分類號(hào)：V231．3文獻(xiàn)標(biāo)識(shí)碼：Adoi：10．13477／j．cnki．a(chǎn)eroengine．2017．02．009StudyonPerformanceSimulationandShockModeIforAxial—FlowCompressorJIANGZhu—yul，F(xiàn)ANZhao—linl，LIUB02(1．ChinaAerodynamicsResearchandDevelopmentCenter，Mi
4、anyangSichuan621000，China；2．SchoolofPowerandEnergy，NorthwesternPolytechnicalUniversity，Xi’an710072，China)Abstract：Inordertoquicklyandaccuratelypredictperformanceandshocklossforaxial—compressor,basedonaxial-flowcompressorS2flowsurfacestreamlinecurvaturemethod．
5、simulationoftheperformanceofatwo-stagetransonicfanwasperformedinvolvingnormalshockmodelandimproveddual-shockmodel．ThustheoveraUperformanceandaerodynamicparametersonnear-designandnear-chokepoint,separatelyat100％and99．76％designrotationspeed，andcharacteristiccur
6、vesat95％，l10％，andl10％designspeedwereobtained．nedifferencesinpredictionofshocklossandcalculationoffan／compressorperformancebetweenthetwoshocklossmodelshavebeenanalyzedbycomparingthesimulationresultsandexperimentdata．Theresultsshowthatonthenear-designpoint．with
7、thenormalshockmodel．calculationresultofradialdistributionoflOSSisclosetotestresult,andresultsoftotalpressureratioandtotalefficiencyareproximatelylowerthantestresultby1．96％and2．54％separately．Thus．thenormalshockmodelearlsatislyengineeringneed．Whileonthenear-cho
8、kepoint,withimpmveddual-shockshockmodel，calculationresultoftotallossisclosertotestresult,resultoftotalpressureratioisconsistentwithtestresult．a(chǎn)ndresultoftotalefficiencyisabout7．28％highert
