Research On Combustible Scheme Of Partition Dual-mode Scramjet

Scramjet is a new aspirated propulsion device which can achieves hypersonic flight in theatmosphere.It is the research peak of modern propulsion technology.Supersonic combustiontechnology is the key of those study.In this paper,we put forward a new concept of the partitiondual-mode scramjet and accomplish the design of the corresponding dimensional model.Then weconduct a series of studies of the model.The main work and conclusions are summarized as follows:First,we study the flow characteristics of the dimensional partition dual-mode scramjet andimprove it by changing the height of the step and the type of the split ring.The study found that:Whenthe step’s height is48mm and the split ring’s length is150mm,the flow characteristics arerational.When the flow ratio is5:1,mach number are2.5and1.3of the up and down channel, the flowforms recirculation zone/ramjet zone and scramjet zone.The transition zone has reasonable velocityshear layer.Secondly,we study the concentration field characteristics of the dimensional partition dual-modescramjet and improve it by changing the injection scheme.The study found that:When the nozzlesare staggered distributed on the wall of the isolator and split ring along radial direction, theconcentration field characteristics are rational.It is oil-rich in the recirculation zone,evenly distributedin the ramjet/scramjet and transition zone.This is conducive for the heat spontaneous combustion inthe recirculation zone, heating the ramjet/scramjet zone and flame spread in those zone.Finally itrealize the stable efficient combustion in the dual-mode combustor.Finally,we study the influence of the combustion performance when changing the injectionmethod/GOR and inlet conductions.The study found that:When the diameter of the nozzle is0.3mm,the number of the nozzle are10,the nozzle are staggered distributed along radial direction andthe oil pressure of the nozzle is1.5MPa, the temperature distribution in the combustor is quiteuniform.When the GOR is0.03,the combustion efficiency of the combustor is quite high.When themuch number increase, the exothermic zone in the combustor move backword,the exothermic amountincrease and the combustion efficiency reduce.Those study indicate that the partition dual-mode combustion is a reasonable and efficiencysupersonic combustion method.It is conductive for improve the stability and efficiency of thesupersonic combustion.It has great guidance for the Scramjet schedule and structural design.