Continuous Detonation of CH4/H2-Air Mixtures in an Annular Combustor with Varied Geometry
F. A. Bykovskii, S. A. Zhdan, E. F. Vedernikov
Lavrentyev Institute of Hydrodynamics, Siberian Branch, Russian Academy of Sciences, Novosibirsk, 630090 Russia
Keywords: непрерывная спиновая детонация, метан, водород, воздух, поперечные детонационные волны, геометрия кольцевой камеры сгорания, система подачи топлива, фоторегистрация, структура течения, тяговые характеристики, continuous spin detonation, methane, hydrogen, air, transverse detonation waves, geometry of the annular combustor, fuel injection system, photorecording, flow structure, thrust characteristics
Abstract
Regimes of continuous detonation of CH4/H2-air mixtures with mass fractions of H2 in the fuel equal to 0 ÷ 1/5 are obtained in an annular combustor 503 mm in diameter with variation of the combustor geometry. The influence of the combustor geometry on the velocity and number of transverse detonation waves, pressure in the combustor, and specific impulse is considered. It is found that three-fold constriction of the combustor exit cross area allows obtaining two-wave regimes of continuous spin detonation in the pure methane-air mixture. Based on stagnation pressures measured at the combustor exit, the specific impulses in the case of continuous detonation are determined for different compositions of the fuel.
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