Characteristics of a supersonic model combustor with two-staged injections of supercritical kerosene

	Characteristics of a supersonic model combustor with two-staged injections of supercritical kerosene
	Zhang TC(张泰昌); Yuan YM(袁越明); Li JG(李建国); Fan XJ(范学军); Zhang TC(张泰昌)
会议录名称	48th AIAA/ASME/SAE/ASEE Joint Propulsion Conference and Exhibit 2012
	2012
页码	1-12
会议名称	48th AIAA/ASME/SAE/ASEE Joint Propulsion Conference and Exhibit 2012
会议日期	JUL 30-AUG 01, 2012
会议地点	Atlanta, GA, United states
摘要	Staged fuel injection plays an important role in designing of a scramjet combustor with balanced performance of combustion efficiency, flame stability, engine unstart, heat release distribution and subsonic/supersonic combustion mode transition. In this paper, a Mach 2.5 model combustor with two-staged fuel injections has been tested in airflow of total temperatures of 1500 K and total pressures of 1.3 MP. Supercritical kerosene with temperature of about 760 K was injected through two integrated fuel injection/flame-holder cavity modules. The effects of fuel injection distribution (injector spacing and fuel ratio) on the combustion pressure rise, thrust increment, lean blowout limit, wall temperature distribution and engine "unstart have been examined.
课题组名称	LHD超声速燃烧
资助信息	American Institute of Aeronautics and Astronautics (AIAA)
ISBN号	9781600869358
URL	查看原文
收录类别	EI
语种	英语
文献类型	会议论文
条目标识符	http://dspace.imech.ac.cn/handle/311007/48274
专题	高温气体动力学国家重点实验室
通讯作者	Zhang TC(张泰昌)
推荐引用方式 GB/T 7714	Zhang TC,Yuan YM,Li JG,et al. Characteristics of a supersonic model combustor with two-staged injections of supercritical kerosene[C]48th AIAA/ASME/SAE/ASEE Joint Propulsion Conference and Exhibit 2012,2012:1-12.

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