Effect of ramp-cavity on hydrogen fueled scramjet combustor  

作　　者：J.V.S.Moorthy B.Rajinikanth B.V.N.Charyulu G.Amba Prasad Rao 

机构地区：[1]Scientist,Defence Research and Development Laboratory,Hyderabad,Andhra Pradesh 500058,India [2]Professor in Mechanical Engineering,National Institute of Technology,Warangal,Andhra Pradesh 506004,India

出　　处：《Propulsion and Power Research》2014年第1期22-28,共7页推进与动力（英文）

摘　　要：Sustained combustion and optimization of combustor are the two challenges being faced by combustion scientists working in the area of supersonic combustion.Thorough mixing,lower stagnation pressure losses,positive thrust and sustained combustion are the key issues in the field of supersonic combustion.Special fluid mechanism is required to achieve good mixing.To induce such mechanisms in supersonic inflows,the fuel injectors should be critically shaped incurring less flow losses.Present investigations are focused on the effect of fuel injection scheme on a model scramjet combustor performance.Ramps at supersonic flow generate axial vortices that help in macro-mixing of fuel with air.Interaction of shocks generated by ramps with the fuel stream generates boro-clinic torque at the air&liquid fuel interface,enhancing micro-mixing.Recirculation zones present in cavities increase the residence time of the combustible mixture.Making use of the advantageous features of both,a ramp-cavity combustor is designed.The combustor has two sections.First,constant height section consists of a backward facing step followed by ramps and cavities on both the top and bottom walls.The ramps are located alternately on top and bottom walls.The complete combustor width is utilized for the cavities.The second section of the combustor is diverging area section.This is provided to avoid thermal choking.In the present work gaseous hydrogen is considered as fuel.This study was mainly focused on the mixing different fuel injection locations.It was found that injecting fuel upstream of the ramp was beneficial from fuel spread point of view.

关 键 词：Supersonic combustion Combustion instabilities RAMPS CAVITIES MIXING 

分 类 号：V23[航空宇航科学与技术—航空宇航推进理论与工程]