Experimental Study on Effects of Fuel Injection on Scramjet Combustor Performance

作     者：Wu Xianyu Li Xiaoshan Ding Meng Liu Weidong Wang Zhenguo 

作者机构：College of Aerospace and Material Engineering National University of Defense Technology ChangSha 410073 China 

出 版 物：《Chinese Journal of Aeronautics》 (中国航空学报（英文版）)

年 卷 期：2007年第20卷第6期

页      面：488-494页

核心收录：

学科分类：08[工学] 082501[工学-飞行器设计] 0802[工学-机械工程] 0825[工学-航空宇航科学与技术] 0801[工学-力学（可授工学、理学学位）] 

基　　金：863 National Project Founds (2005AA723070) 

主　　题：scramjet combustor fuel injection direct-cormect test 

摘      要：In order to investigate the effects of fuel injection distribution on the scrarnjet combustor performance, there are conducted three sets of test on a hydrocarbon fueled direct-connect scramjet test facility. The results of Test A, whose fuel injection is carried out with injectors located on the top-wall and the bottom-wall, show that the fuel injection with an appropriate close-front and centralized distribution would be of much help to optimize combustor performances. The results of Test B, whose fuel injection is performed at the optimal injection locations found in Test A, with a given equivalence ratio and different injection proportions for each injector, show that this injection mode is of little benefit to improve combustor performances. The results of Test C with a circumferential fuel injection distribution displaies the possibility of ameliorating combustor performance. By analyzing the effects of injection location parameters on combustor performances on the base of the data of Test C, it is clear that the injector location has strong coupled influences on combustor performances. In addition, an irmer-force synthesis specific impulse is used to reduce the errors caused by the disturbance of fuel supply and working state of air heater while assessing combustor performances.