超燃冲压发动机燃烧室流场数值模拟.pdf

1、南京航空航天大学硕士学位论文超燃冲压发动机燃烧室流场数值模拟姓名：杨事民申请学位级别：硕士专业：航空宇航推进理论与工程指导教师：唐豪20080301超燃冲压发动机燃烧室流场数值模拟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