IMECH-IR  > 高温气体动力学国家重点实验室
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)
Source Publication48th AIAA/ASME/SAE/ASEE Joint Propulsion Conference and Exhibit 2012
2012
Pages1-12
Conference Name48th AIAA/ASME/SAE/ASEE Joint Propulsion Conference and Exhibit 2012
Conference DateJUL 30-AUG 01, 2012
Conference PlaceAtlanta, GA, United states
AbstractStaged 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.
DepartmentLHD超声速燃烧
Funding OrganizationAmerican Institute of Aeronautics and Astronautics (AIAA)
ISBN9781600869358
URL查看原文
Indexed ByEI
Language英语
Document Type会议论文
Identifierhttp://dspace.imech.ac.cn/handle/311007/48274
Collection高温气体动力学国家重点实验室
Corresponding AuthorZhang TC(张泰昌)
Recommended Citation
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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