超燃沖壓發(fā)動(dòng)機(jī)燃燒室流場(chǎng)數(shù)值模擬.pdf

1、南京航空航天大學(xué)碩士學(xué)位論文超燃沖壓發(fā)動(dòng)機(jī)燃燒室流場(chǎng)數(shù)值模擬姓名：楊事民申請(qǐng)學(xué)位級(jí)別：碩士專(zhuān)業(yè)：航空宇航推進(jìn)理論與工程指導(dǎo)教師：唐豪20080301超燃沖壓發(fā)動(dòng)機(jī)燃燒室流場(chǎng)數(shù)值模擬IIABSTRACTSramjetenginewasannewPropulsionTechnologywiththebroaddevelopmentprospects.Inthisarticlethefuelmixtureburningflowfieldcar

2、riedonsimulationtheresearchtothecombustionchamberinsupersonicinletcondition.Combustionchamberflowfieldwascarriedonnumericalsimulationinviewoftheapproximateonedimensionalmodelanalysisthroughonedimensionalprocedurethecombu

3、stionchamberincludingtheIsolatthecombustionchamberthepartialjetpipe.ThisarticlestheequalpressureequalManumberequalstatictemperaturemodel.Theconclusionswereasfollows:Inthecombustionchambertherewasmuchtotalpressurelosethem

4、eimptMachthemetotalpressureloses.TheboundarylayermovedalongwiththeheatingquantityincreasetotheupstreaminIsolatfinallymaymovetotheinletpipeinlet.Inthispaperitmaytransfmduringdifferentmodesthroughchangingburningexothermicf

5、thefixedgeometrythroatmodel.IndertofurtherstudyftheflowfieldacteristicthisarticlehadresearchtothetwodimensionalcombustionchambermodelseparatelyincoldconditionburningconditionsimultaneouslyhasalsostudiedtheIsolatflowfield

6、thefunction.IncoldconditionfirstlycomparingseveralcomputationalmethodfNumericalsimulationresultchoosingtheappropriatemethodtocomputeranalysethemodel.Theacteristicofresistance、totalpressure、temperatureiscomputedanalysedth

7、roughtheprogramcodeFluentsoftthemodelwasadvantageoustothefuelmixburning.Theconclusionswereasfollows:NNDschemewasmucheffectatsimulationshockwaveacteristictheMUSCLschemewasmucheffectatcomputationviscousnessflowsburningflow

8、.Thecavitystructurecaneffectivelystrengthenthefuelmixingburningcamparingthetwostepstructure.IntheIsolattherewastheseparationofboundarylayerphenomenonobviouslysimultaneouslyitappearedcomplexshocktrainstructurewiththebound

9、arylayerthisshocktraincancushioninfluencefinletpipefromthehighbackpressureofburningwhichcantransfmindifferentmodesbutalsoshouldsee:iftheshocktrainwaspushedtotheIsolatitwillbeabletocausetheenginenottostart.Thestepstructur

10、ecouldhindereffectivelyburninghighbackpressuretomovetotheupstreamThecoldconditionflowfieldtheburningconditionflowfieldweremuchdifferentincoldconditionflowingithadverystrongshockwaveeffectthusthetotalpressureloseswasmuchh

11、ightheresistancecoefficientwasmuchbig.Contrarilyinburningconditioninthecavitystructurethespeedofflowreducesfburningheatingtheshockwaveeffectwasmuchweak.Thisarticlecontrastlyanalyzeseveralkindofcavitymodelsseveralinjectin

12、gfuelwayfthecavitythebeststeadyflameeffectffuelburningwassummarized.Theintegratedanalysisindicatedthatcavitystructurecombustionchamberwaspossibletorealizethefuelmixingburningfscramjettheonedimensionalmodelanalysiscanrefl

13、ectthetheparameterchangeruleintuitivelyfentirecombustionchamber.Thecavitystructurewasthesteadyflameidealstructureithadtheextremelysignificancetosupersonicburning.KeyWds:supersoniccombsionscramjetNumericalsimulationcavity