Effects of Staged Injection on Supersonic Mixing and Combustion  

作　　者：HOU Lingyun Bernhard WEIGAND Marius BANICA 

机构地区：[1]School of Aerospace, Tsinghua University, Beijing 100084, China [2]lnstitut fiir Thermodynamik der Lufi- and Raumfahrt （ITLR）, Universitaet Stuttgart, Stuttgart 70569, Germany [3]TEB42 Liquid Propulsion Systems, EADS Astrium Space Transportation, Les MureauxCedex 78133, France

出　　处：《Chinese Journal of Aeronautics》2011年第5期584-589,共6页中国航空学报（英文版）

基　　金：National Natural Science Foundation of China(50306011);the German Research Foundation (DFG) (GRK1095/1)

摘　　要：The three-dimensional （3D） reacting flow in a staged supersonic combustor is examined numerically. In order to obtain the optimum stream-wise vortices, a swept ramp injector is chosen as the second-stage wall injection combined with the first-stage central strut injection. The performance of the two-staged injection is compared with that of a one-staged injection, while the strut is kept installed in both cases. The two-staged injections can make full use of the residual oxygen near the wall and release more heat. The second-stage injection further downstream avoids the strong shock waves in the isolator and results in a rising wall pressure and good burning effects after the wall injection. Therefore, it allows more fuel to be injected into the supersonic combustor without causing thermal choking. Parallel injection from the second-stage swept ramp shows low total pressure loss and the best burning efficiency, compared with the other injection angles.The three-dimensional （3D） reacting flow in a staged supersonic combustor is examined numerically. In order to obtain the optimum stream-wise vortices, a swept ramp injector is chosen as the second-stage wall injection combined with the first-stage central strut injection. The performance of the two-staged injection is compared with that of a one-staged injection, while the strut is kept installed in both cases. The two-staged injections can make full use of the residual oxygen near the wall and release more heat. The second-stage injection further downstream avoids the strong shock waves in the isolator and results in a rising wall pressure and good burning effects after the wall injection. Therefore, it allows more fuel to be injected into the supersonic combustor without causing thermal choking. Parallel injection from the second-stage swept ramp shows low total pressure loss and the best burning efficiency, compared with the other injection angles.

关 键 词：supersonic mixing stream-wise vortices staged injection swept ramp COMBUSTION 

分 类 号：V235.21[航空宇航科学与技术—航空宇航推进理论与工程] TP393.092[自动化与计算机技术—计算机应用技术]