跨聲速微型斜流壓氣緩怋.pdf

1、南京航空航天大學博士學位論文跨聲速微型斜流壓氣緩怋姓名：陳杰申請學位級別：博士專業(yè)：航空宇航推進理論與工程指導教師：梁德旺201010跨聲速微型斜流壓氣機設計方法研究IIAbstractMicroturbineenginehastheadvantagesoflightweightlargepowerhighenergydensitysoithasabroadapplicationprospectinmilitarycivil.Compr

2、essoneofthekeycomponentsalmosttakesthetypeofcentrifugalmixedflow.Thepressureratioofthemajityofmicrocompressisunder4.IncreasingthepressureratiocanimprovethethermalefficiencyofthewholecyclereducetheSFCincreasethethrustsoth

3、egoalofmicrocompressdevelopmentistoincreasethetipspeedto500msmemakeitspressureratioover4.Therefethispaperinvestigatedesignmethodsoftransonicmicromixedflowcompresswhosepressureisover4bybothnumericalsimulationexperimentmai

4、nlyinthefollowingaspects:Firstlythedesignframewkoftransonicmicroimpellerhasbeenconstructedbasedon3dflowfieldcalculationincludingtheprimarydesignthemeridionalchanneldesignbladedesignetc.Theeffectsofbladenumbermeridionalch

5、annelthedistributionofloadingthicknessofroottransonicbladeprofileofthetipsplitterbladeotherparametersontheperfmanceoftheimpellerflowfield.Accdingtothecomparisonanalysisthedesignmethodbasicprincipleofeachparameterisobtain

6、ed.ThemicroimpellerMJM1wasalsodesignedwhosediameteris12cm.Numericalsimulationshowsthatthehighestpressureratiooftheimpellerisover5theefficiencyishigherthan80%inmostwkingconditions.Secondlytheinnerflowfieldofthemicrodiffus

7、erM0Awiththeusualtypewasanalyzed.Thefactsthataffecttheperfmanceofmicrodiffuserarefoundthusthisthesisputsfwardtheconfmalpassagediffuser.the3Dmethodofthediffuserisestablishedregardingflowchannelasdesignobjecttheinfluenceof

8、thepassageareaangledistributiononthediffuserperfmancewasinvestigated.Itshowsthatthepassageareadistributionplaysameimptantroleindiffuserperfmancethanthepassageangletheareadistributionofslowincreaseafterthefirstrapidincrea

9、secangethigherperfmance.TheexperimentaldatashowsthattheM0AisreplacedwiththeconfmalpassagediffuserM0Cthethrustoftheengineatthemaximumspeedcanincrease11%theSFCcanreduceby9%.TheearlydesignofthediffuserMJM1showsthatitcangeta

10、highertotalpressurerecoverycoefficientthan0.93thepressurecoefficientisabout0.55.ThirdlythedesignedcompressisusedinMJM1microturbineengine.Afterimprovingthepropanegassupplymethodthematchingrelationshipbetweencombustioncham