Continuous-Detonation Combustion of Hydrogen: Results of Wind Tunnel Experiments
S. M. Frolov1,2, V. I. Zvegintsev3, V. S. Ivanov1, V. S. Aksenov1,2, I. O. Shamshin1,2, D. A. Vnuchkov3, D. G. Nalivaichenko3, A. A. Berlin1, V. M. Fomin3
1Semenov Institute of Chemical Physics, Russian Academy of Sciences, Moscow, 119991 Russia
2National Research Nuclear University "MEPhI", Moscow, 115409 Russia
3Khristianovich Institute of Theoretical and Applied Mechanics, Siberian Branch, Russian Academy of Sciences, Novosibirsk, 630090 Russia
Keywords: прямоточный воздушно-реактивный двигатель, сверхзвуковое течение, детонация, водород, удельный импульс, тяга, аэродинамическая труба, ramjet, supersonic flow, detonation, hydrogen, specific impulse, thrust, wind tunnel
Abstract
Firing tests of a ramjet model 1.05 m long and 0.31 m in diameter with an expanding annular combustor operating in the regime of detonation combustion of hydrogen are described. The test are performed in a short-duration wind tunnel at free-stream Mach numbers of the incoming air flow from 5 to 8 and stagnation temperature of 290 K. Continuous-detonation and streamwise-oscillating regimes of hydrogen combustion with characteristic frequencies of 1250 and 900 Hz, respectively, are observed. The maximum measured values of the fuel-based specific impulse and the thrust generated by the engine are 3600 s and 2200 N, respectively.
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