Investigation of High-Speed Ramjet Engines
Investigation of High-Speed Ramjet Engines
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DOI：
10.1007/s10573-010-0054-0
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发表时间：
2010-09
期刊：
影响因子：
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通讯作者：
V. Avrashkov;E. Metelkina;D. V. Meshcheryakov
中科院分区：
文献类型：
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作者：
V. Avrashkov;E. Metelkina;D. V. Meshcheryakov
本文简要概述了莫斯科航空学院 (MAI) 进行的高速冲压喷气发动机燃烧室的研究和开发。给出的阴影照片显示了氢燃烧过程中规则冲击结构相对于流的热量输入的变化。通过可视化 OH 自由基发光来研究斜冲击波对燃烧的影响。由于燃烧效率对流动参数和结构的显着依赖，因此研究具有燃烧室可变气流管道的冲压喷气发动机设计具有重要意义，它允许调整工作部分以获得在广泛的飞行条件下所需的参数和特性。法国和俄罗斯的联合项目已经对这种燃烧室进行了一系列的测试。给出了与飞行马赫数 2-7 相对应的测量结果。使用化学纯甲烷和氢气的混合物作为燃料。介绍了 MAI 开发的用于测试大范围燃烧室的三级模型流加热器的特性。
This paper gives a brief overview of investigations and developments of combustion chambers of high-speed ramjet engines performed at Moscow Aviation Institute (MAI). Shadow photographs are given which show changes in the structure of regular shocks versus heat input to the flow during hydrogen combustion. The impact of oblique shock waves on combustion is studied by visualizing OH radical luminescence. Because of the significant dependence of the combustion effectiveness on the flow parameters and structure, it is relevant to study ramjet engine designs with a variable air flow duct of the combustion chamber, which allows adjustment of the working section to obtain the required parameters and characteristics over a wide range of flight conditions. A large series of tests of such combustion chambers have been performed under a joint French—Russian program. Measurement results corresponding to flight Mach numbers 2–7 are given. Mixtures of chemically pure methane and hydrogen was used as fuel. Characteristics of a three-stage heater of model flow developed at MAI for testing wide-range combustion chambers are presented.