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1、AircraftDesign4(2001)115–126High-bypassturbofanmodelusingafanradial-profileperformancemapab,bbB.Curnock,J.Yin*,R.Hales,P.PilidisaRolls-Royceplc,Bristol,UKbSchoolofMechanicalEngineering,CranfieldUniversity,Cranfield,BedfordshireMK43OAL,UKAbstractAccurategasturbineperformancemodelsbasedonthermodynamicpr
2、inciplescanbringmanybenefits.Insuchmodelsitisanormalpracticetorepresentthedifferentcomponentsbymeansofitsperformancemapsorcomponentcharacteristicsdescribingtherelationshipsbetweenthethermodynamicvariablesrepresentingthecomponent.Itiswellknownthatthefansofhigh-bypassengineshavestrongradialprofilesofall
3、thermodynamicvariables.Itiscommontoaveragetheseprofilessothatoneortwocharacteristicmapscanrepresentthefan.Thepresentpaperdescribeshowtheradialprofilescanbeusedtomakeanestimationofturbofanperformance.Theresultsaresomewhatdifferenttothoseproducedusingacomponentperformancemaps.r2001ElsevierScienceLtd.All
4、rightsreserved.1.IntroductionThefan,orlow-pressurecompressor,ofhigh-bypass-ratiojetenginesinlarge,wide-bodied,civilaircraftisasinglestage,lowhub-to-tipratioturbomachine.Itexhibitssignificantradialvariationsinperformance.Ingasturbineperformancemodelling,itiscommonpractice[1–6]torepresentthefanasaone-
5、dimensionalcomponentortwoseparatecompressorswithone-dimensionalflowcharacteristics,abypassfanandacorefan,wherethecorefandeliversthecoreflowandthebypassfandeliversthebypassair.Eachcompressorhasitsowncharacteristic.Methodssuchas[7]areavailabletoproducethebypassandcorecharacteristic.Inothercases,recogni
6、singthattheflowisnotuniform,researchers*Correspondingauthor.Tel.:+44-1234-750111ext5311;fax:+44-1234-752407.E-mailaddress:j.yin@cranfield.ac.uk(J.Yin).1369-8869/01/$-seefrontmatterr2001ElsevierScienceLtd.Allrightsreserved.PII:S1369-8869(01)00007-6116B.Curnocketal./AircraftDesign4(2001)115–126Nomencla
7、tureBPRbypassratioCNrelativeshaftspeedCMFFcumulativemassflowfractionWmassflowPRpressureratioRsrelativefanrotorradiumNshaftspeedTtotaltemperaturePtotalpressureSFCspecificfuelconsumptionTETturbineentrytotaltempe
