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1、V-t别、”r子令蜘，匆’‘计/口一“阎布行‘睁、!姚尹叔铡劫乏喷气厂久仲t，Lt1,15}T一2-,1Plfr-Z311%带Dt1k、t}z,-7,-rz[}‘)及ce'7Iiz、‘了衣亏/刁、P&q、、。渺或、{矽咨科，9},rq、习:}y'l啦域_切ti飞Iii沙e-P、丝_wBeijingUniversityofAeronauticsandAstronautics,Master'sDissertationABSTRACTInthisdissertation,wedesignedamicro-turbo
2、enginehavingthethrust10棺tofulfilltherequirementsofthenextgenerationmilitarysmallaircraft,drones,airtoairmissilesandotherkindsofciviltransportorsportsvehiclesatthegroundorwatersurfaceNowadays,therearethreestepstobeperformedfordesignaturbo-engineinanoverallle
3、vel.Wecancallittheintegraldesignortheoveralldesignofanengine.Theyarethermodynamicanalysis,characteristiccalculationorperformancesimulation.Theyputforwardthecomponentdesignparametersforaseriesofcomponentdesignworking.Thefirstmajordesignstepofthisworkistocarr
4、youtthethermodynamicdesignpointstudiesofcycleanalysis.Thesearedetailcalculationstakingintoaccountallimportantfactorssuchasexpectcomponenteficiencies,pressurelossesandwouldbecarriedoutoverarangeofpressureratioandturbineinlettemperature.Avalueforthespecificth
5、rustandspecificfuelconsumptionisdeterminedforvariousvaluesofthecycleparameters.Bydoingthisstep,wecanestimatetheroughperformanceoftheintegralengine.Hereweusetheprogramcodethatadaptsandre-organizesallthetheoreticalnon-idealcycleanalysisschemeforturbojetandtur
6、bofanengineinFORTRANlanguage.Thesecondstepistoconsidertheoveralldesignofenginecomponentsandstructuralconsiderations.Knowingthecomponenteficiencies,pressureratioandturbineinlettemperature,atentionturnedtotheaerodynamicdesignoftheturbomachinery.Oncewehavesetl
7、edonasuitablechoiceofthermodynamiccycleoutputparameters,wecanmakeuseofthespecificthrustoutputtodeterminethemassflowraterequiredtogivethethrustas10kg.Byexperience,weprescribedthediameterofthecentrifugalcompressorandthedesignedrotortiplinearspeedwerepossiblet
8、odeterminetherotationalspeedofthecentrifugalcompressor.Besideswecandesigntheoverallaerodynamicsdesignofthecentrifugalcompressorandsingle-stageaxialflowturbine.Herewehavewritentheturbinecycleprogram,itw
