2018傳熱傳質(zhì)學(xué)年會(huì)集

學(xué)學(xué)術(shù)會(huì) ，，（中國(guó)運(yùn)載火箭技術(shù)研究，( , ：射流微通道01部件，共布置4個(gè)節(jié)點(diǎn)，分別在散熱器加熱壁面0，散熱器1，散熱器2，散熱器6789。圖1 （）為系統(tǒng)其中的節(jié)點(diǎn)

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圖2動(dòng)態(tài)仿真系統(tǒng)連接圖W/(Km2)W/(Km2)，30000W/(K·m2)3對(duì)比了冷凝溫度穩(wěn)定為20℃，系統(tǒng)在不同體積流量下，即換熱系數(shù)不同時(shí)，熱控系統(tǒng)所能1030000W/(Km2)1400W的熱量。圖3換熱系數(shù)對(duì)散熱極限的影 圖4冷凝溫度對(duì)散熱極限的影510mL1000mL時(shí)，在受到相同階躍熱負(fù)荷的條件下熱源面的圖5儲(chǔ)液器容量對(duì)散熱的影響3種常用的管路下系統(tǒng)壓力損失和4mm的不銹，以及管外徑3mm、內(nèi)徑2mm的不銹。6對(duì)比了采用不同管路的射流微通道流體回路系統(tǒng)總壓力損失和射流微通道散熱器10%7對(duì)比了射流微通圖6管徑與體積流量對(duì)壓力損失的影 圖7管徑對(duì)系統(tǒng)質(zhì)量和壓力損失的影3決航天器上局部高熱流密度散熱具有有效地本文通過機(jī)理分析和模型簡(jiǎn)化建立了系統(tǒng)[1]YehL.Reviewofheattransferinelectronicequipment[J].JElectronPackaging,1996,117(4):[2]．射流冷卻技術(shù)研究[J]．航空計(jì)算技術(shù)，2006,36(3):4-TianFeng.ResearchonSprayCoolingTechnigues[J].AeronauticalComputingTechnigue,2006,36(3):4-RobinsonAJ,SchnitzlerE.AnExperimentalInvestigationof andSubmergedMiniatureLiquidJetArrayImement[J].HeatTransferExperimentalThermalandFluidScience,2007,32:1-13TuckermanDB,PeaseR.High-performanceheatsinkingforVLSI[J].IEEEElectrondeviceletters,1981,2(5):SungMK,MudawarI.Single-phaseandtwo-phasecoolingusinghybridmicro-channel/slot-jetInternationalJournalofHeatandMassTransfer,2008,51(15):3825-SungMK,MudawarI.Single-phaseandtwo-phaseheattransfercharacteristicsoflowtemperaturehybridmicro-channel/micro-jetimementcoolingmodule[J].InternationalJournalofHeatandMassTransfer,2008,51(15):3882-3895SungMK,MudawarI.Effectsofjetpatternonsingle-phasecoolingperformanceofhybridmicro-channel/micro-circular-jet-imementthermalmanagementscheme[J].InternationalJournalofHeatandMassTransfer,2008,51(19):4614-4627SungMK,MudawarI.CHFdeterminationforhigh-heatfluxphasechangecoolingsystemincorporatingbothmicro-channelflowandjetimement[J].InternationalJournalofHeatandMassTransfer,2009,52(3):610-,,于新剛等.神舟載人飛船流體回路動(dòng)態(tài)仿真研究[J].載人航天,2014(3):228-FuYang,FanYufeng,YuXinga