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1、JOURNALOFPROPULSIONANDPOWERVol.14,No.1,January–February1998DigitalSimulatorforSteady-StatePerformancePredictionofMilitaryTurbofanEngineVivekSanghi,*B.K.Lakshmanan,†andV.Sundararajan‡GasTurbineResearchEstablishment,Bangalore-560093,IndiaThesignicanceofpropulsionsystemste
2、ady-stateperformancepredictionhasbeenidentied.Thedigitalsimulationtechniqueshavebeendescribedforsteady-stateperformanceprediction,withcompo-nentmapsandacontroller.Inadditiontoperformanceprediction,theapplicationofasimulationcodehasbeendemonstratedtoanenginecycleredesign
3、ingcasestudywithoutmajormodicationsinalreadyexistinghardware.Asperthecurrentmilitaryapplicationtrends,thetwin-spoolturbofanwithamixedexhausthasbeenchosenasthepropulsionconcept.Theproposedformulationcaneasilybemodiedtosimulatethesteady-stateperformanceofthetwin-spoolturb
4、ojetengineandalsotogeneratethecontrolschedulesintheearlydesignstage.Nomenclatureuration,whilethespecicfuelconsumptionwillhaveasig-nicantbearingonitsrangeandendurancecharacteristics.A=areaALT=altitudeThus,propulsionsystemsteady-stateperformanceplaysaveryCD=nozzleowblocka
5、gefactorsignicantroleindeterminingthemissionperformanceoftheCp=specicheataircraftwithwhichitisintegrated.F=thrustThepropulsionsystemperformanceisthefunctionofitsg=gravitationalconstantcycleparameters.Themixed-owtwin-spoolturbofanisaH=enthalpymorewidelyacceptedpropulsion
6、conceptformilitaryappli-J=Joule’sconstantcations,thoughtwin-spoolturbojetmaybemoresuitableforM=ightMachnumbermissionapplicationswithhighsupersonicMachnumbers,dur-N=rotationalspeedingwhichaircraftisrequiredtospendagreaterportionofP=totalpressureighttimeinasupersonicregim
7、e.PR=nozzlepressureratioIntheconceptualdesignphase,whereemphasisismainlyp=staticpressureonparametricstudiesforcongurationdenitionandprelim-R=gasconstantinarysizing,ageneralizedandrobustenginemodel,likethe1T=totaltemperatureonereportedinSanghi,thatworksoverawideightenvel
8、opet=statictemperatureandoveralargeparametricvariationinenginecyclevariables,V=owvelocityisrequired.Thecritica
