在接近2马赫和1.5马赫的气流下，带环形爆轰燃烧室的氢燃料冲压发动机的多维模拟和试验火焰

PROGRESS IN DETONATION RESEARCH Pub Date : 2020-10-16 DOI:10.30826/icpcd12a23

V. Ivanov, V. S. Aksenov, S. Frolov, P. Gusev, I. O. Shamshin, A. E. Zangiev

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引用次数: 0

摘要

现代高速无人飞行器采用小型涡轮喷气发动机或冲压喷气发动机提供动力。现有的冲压发动机在热力学循环中运行，在恒压下进行燃料的反聚合燃烧，在飞行马赫数M约为2至6时是有效的。

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MULTIDIMENSIONAL SIMULATIONS AND TEST FIRES OF A HYDROGEN-FUELED RAMJET WITH AN ANNULAR DETONATIVE COMBUSTOR AT APPROACHING AIR FLOW OF MACH 2 AND 1.5

Modern high-speed unmanned aerial vehicles are powered with small-size turbojets or ramjets. Existing ramjets operating on the thermodynamic cycle with de§agrative combustion of fuel at constant pressure are efficient at flight Mach numbers M ranging from about 2 to 6.

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PROGRESS IN DETONATION RESEARCH

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