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.

中文翻译：

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CH4/H2-空气混合物在不同几何形状的环形燃烧器中的连续爆轰

在直径为 503 毫米的环形燃烧器中，随着燃烧器几何形状的变化，CH4/H2-空气混合物的连续爆轰机制在燃料中的 H2 质量分数等于 0-1/5。考虑了燃烧器几何形状对横向爆震波的速度和数量、燃烧器中的压力和比冲的影响。发现燃烧器出口横截面积的三倍收缩允许在纯甲烷 - 空气混合物中获得连续自旋爆炸的两波状态。根据在燃烧器出口处测得的停滞压力，确定连续爆轰情况下不同燃料成分的比冲量。