热射流点火对多循环爆震管内火焰传播特性的影响

推进技术 ›› 2015, Vol. 36 ›› Issue (12): 1846-1851.

热射流点火对多循环爆震管内火焰传播特性的影响

赵炜¹,韩启祥¹,王家骅¹,贾冰岳²,宫继双²

南京航空航天大学能源与动力学院，江苏南京210016,南京航空航天大学能源与动力学院，江苏南京210016,南京航空航天大学能源与动力学院，江苏南京210016,中国航天科工集团三十一研究所，北京100074,中国航天科工集团三十一研究所，北京100074

发布日期:2021-08-15
作者简介:赵炜(1986—)，男，博士生，研究领域为爆震燃烧。
基金资助:
江苏省普通高校研究生科研创新计划资助项目(CXLX11_0215)。

EffectsofHotJetIgnitiononFlamePropagationCharacteristicsinMulti-CycleDetonationTube

Coll.ofEnergyandPower，NanjingUniversityofAeronauticsandAstronautics，Nanjing210016，China,Coll.ofEnergyandPower，NanjingUniversityofAeronauticsandAstronautics，Nanjing210016，China,Coll.ofEnergyandPower，NanjingUniversityofAeronauticsandAstronautics，Nanjing210016，China,The31stResearchInstituteofCASIC，Beijing100074，China and The31stResearchInstituteofCASIC，Beijing100074，China

Published:2021-08-15

摘要/Abstract

摘要： 为研究热射流点火对多循环脉冲爆震特性的影响，在一台工作频率为20Hz的气动阀式PDE上开展了试验研究，重点分析了热射流点火位置与预燃室中敏感性气体的填充比对爆震管内初始火焰传播速度及压力特性的影响。研究结果表明:热射流点火的位置在爆震管头部回流区内，对爆震管内火焰传播速度影响较小，热射流点火位置在回流区外，随着离封闭距离的增加火焰传播速度减小；预燃室填充比从1.78增加到2.75，初始火焰平均速度从380m/s上升到420m/s左右，当填充比在2.75～3.45时，火焰传播速度基本保持不变。

关键词: 热射流；脉冲爆震发动机；点火位置；填充比中图分类号:V231.1文献标识码:A文章编号:1001-4055(2015)12-1846-06DOI:10.13675/j.cnki.tjjs.2015.12.013

Abstract: Inordertostudythecharacteristicsofmulti-cyclepulsedetonationwithhotjetignition，seriesofexperimentswereperformedwithanaero-valvepulsedetonationengineattheoperationfrequencyof20Hz.Theinitialflamepropagationvelocityandpressurecharacteristicswereanalyzedwithdifferenthotjetignitionpo.sitionsandfillfractionofjetsub-chamber.Theexperimentalresultsshowthatthehotjetslightlyaffectstheini.tialflamepropagationvelocity，whichislocatedintherecirculatingzoneintheheadofdetonationtube.Howev.er，theinitialflamevelocitydecreasesasthedistancebetweenhotjetpositionandblindheadincreases，whichislocatedoutsidetherecirculatingzone.Theinitialaverageflamevelocityincreasesfrom380m/sto420m/sasthefillfractionincreasesfrom1.78tO₂.75andchangesslightlyforthefillfractionbetween2.75to3.45.

Key words: Hotjet；Pulsedetonationengine；Ignitionposition；Fillfraction

赵炜,韩启祥,王家骅,贾冰岳,宫继双. 热射流点火对多循环爆震管内火焰传播特性的影响[J]. 推进技术, 2015, 36(12): 1846-1851.

ZHAOWei¹,HANQi-xiang¹,WANGJia-hua¹,JIABing-yue²,GONGJi-shuang². EffectsofHotJetIgnitiononFlamePropagationCharacteristicsinMulti-CycleDetonationTube[J]. Journal of Propulsion Technology, 2015, 36(12): 1846-1851.

参考文献

[1] RoyGD,FrolovSM,BorisovAA,etal.PulseDetona.tionPropulsion:Challenges,CurrentStatus,andFuturePerspective[J].ProgressinEnergyandCombustionSci.ence,2004,30(6):545-672.
[2] DeanAJ.AReviewofPDEDevelopmentforPropulsionApplications[R].AIAA2007-0985.
[3] KaneshigeM,ShepherdJE.DetonationDatabase[R].FM97-8,Pasadena,USA:CaliforniaInstituteofTech.nology,1997.
[4] GelfandBE,KhomikSV,BartenevAM,etal.Deto.nationandDeflagrationInitiationattheFocusingofShockWavesinCombustibleGaseousMixture[J].ShockWaves,2000,10(3):197-204.
[5] CiccarelliG,DorofeevS.FlameAccelerationandTran.sitiontoDetonationinDucts[J].ProgressinEnergyandCombustionScience,2008,34(4):499-550.
[6] SinibaldiJO,BrophyCM,RobinsonLTJP.IgnitionEffectsonDetonationtoDetonationTransitionDistanceinGaseousMixtures[R].AIAA2000-3590.
[7] BrophyCM,SinibaldiJO,NetzerDW,etal.Opera.tionofaJP-10/AirPulseDetonationEngine[R].AIAA2000-3591.
[8] HidetoshiSHIMADA,YasuhiroKENMOKU,HiroyukiSATO.ANewIgnitionSystemforPulseDetonationEn.gine[R].AIAA2004-308.
[9] KnystautasR,LeeJH,MoenI,etal.DirectInitiationofSphericalDetonationbyaHotTurbulentGasJet[J].Symposium(International)onCombustion.Elsevier,1979,17(1):1235-1245.
[10] Zhaowei,HanQixiang,Zhangqi.ExperimentalInves.tigationonDetonationInitiationwithaTransversalFlameJet[J].Combustion,Explosion,andShockWaves,2013,49(3):171-177.
[11] 王治武,陈星谷,郑龙席,等.横向射流起爆爆震波数值研究[J].推进技术,2013,34(3):422-427.(WANGZhi-wu,CHENXing-gu,ZHENGLong-xi,etal.NumericalInvestigationoftheTransverseJetEf.fectsonDetonationInitiationCharacteristics[J].Jour.nalofPropulsionTechnology,2013,34(3):422-427.)
[12] 宫继双,范育新,张义宁,等.脉冲爆震发动机倒旋流气动阀性能实验[J].推进技术,2012,33(4):657-664.(GONGJi-shuang,FANYun-xin,ZHANGYi-ning,etal.ExperimentalInvestigationonInversing-RotatingAero-ValveinPDE[J].JournalofPropulsionTechnology,2012,33(4):657-664.)
[13] 孙健,韩启祥,王家骅,等.助爆装置影响两相混气中爆震波触发特性实验[J].推进技术,2013,34(7):997-1001.(SUNJian,HANQi-xiang,WANGJia-hua,etal.ExperimentalInvestigationonDetona.tionDevicesInduceDetonationinTwo-PhasesMixedGas[J].JournalofPropulsionTechnology,2013,34(7):997-1001.)
[14] LindstedtRP,MichelsHJ.DeflagrationtoDetonationTransitionsandStrongDeflagrationsinAlkaneandAl.keneAirMixtures[J].CombustionandFlame,1989,76(2):169-181.
[15] MatsuokaK,EsumiM,IkeguchiKB,etal.OpticalandThrustMeasurementofaPulseDetonationCombus.torwithaCoaxialRotaryValve[J].CombustionandFlame,2012,159(3):1321-1338.
[16] 严传俊,范玮,郑龙席.脉冲爆震发动机原理及关键技术[M].西安:西北工业大学出版社,2005.
[17] UrtiewPA,OppenheimAK.ExperimentalObserva.tionsoftheTransitiontoDetonationinanExplosiveGas[J].ProceedingsoftheRoyalSocietyofLondon,SeriesA,1966,295(1440):13-28.
[18] 黄玥.脉冲爆震发动机小型化研究[D].南京:南京航空航天大学,2012.
[19] 张宝平,张庆明,黄风雷.爆轰物理学[M].北京:兵器工业出版社.1997.
[20] PantowEG,FischerM,KratzelT.DecouplingandRe.couplingofDetonationWavesAssociatedwithSuddenExpansion[J].ShockWaves,1996,6(3):131-137.
[21] SheenHJ,ChenWJ,JengSY.RecirculationZonesofUnconfinedandConfinedAnnularSwirlingJets[J].AIAAJournal,1996,34(3):572-579.
[22] LIK,TankinRS.AStudyofColdandCombustingFlowAroundBluff-BodyCombustors[J].CombustionScienceandTechnology,1987,52(4-6):173-206.(编辑:梅瑛)