Supersonic Cavity Based Combustion with Kerosene/Hydrogen Fuel  

作　　者：Rajarshi Das Jeong Soo Kim Heuy Dong Kim 

机构地区：[1]Department of Mechanical Engineering,Andong National University [2]School of Mechanical Engineering,Pukyong National University

出　　处：《Journal of Thermal Science》2015年第2期164-172,共9页热科学学报（英文版）

基　　金：supported by Advanced Research Center Program(No.2013073861) through the National Research Foundation of Korea

摘　　要：A comparative study with kerosene and hydrogen fuel in a model scramjet combustor has been carried out nu- merically. The effect of fuel-air equivalence ratio on the flow field properties in a cavity based mixing mechanism at a freestream Math number of 2.08 has been probed. The investigation has been carried out in a two dimension- al numerical model where a cavity of length to depth ratio of 2 is mounted on one of the walls of the flow channel The flow field shock structure is observed to change with the change in fuel-air equivalence ratio. Total pressure loss is observed to depend both on fuel air equivalence ratio and the fuel type. The spread of fuel in the test sec- tion shows marked variation with the equivalence ratio. Performance of injector location on the fuel-air mixing is also probed during the course of the investigation.

关 键 词：SCRAMJET fuel-air mixing KEROSENE HYDROGEN equivalence ratio 

分 类 号：TK16[动力工程及工程热物理—热能工程]