Regimes of continuous spin detonation and continuous multifront detonation in a hydrogen–oxygen mixture are obtained in a plane-radial combustor with an inner diameter of 100 mm and exhaustion toward the periphery. The fuel-lean limits of detonation in terms of the specific flow rate of the mixture are determined. For continuous spin detonation, transverse detonation waves and the flow in their vicinity in the combustor plane are reconstructed. The detonation wave is found to be significantly curved because of the increase in the tangential component of the velocity along the combustor radius. It is demonstrated that the scale effect is manifested only in the number of rotating waves. However, their velocity increases with increasing the combustor size. The velocity deficit of continuous detonation is 20–40% as compared to the velocity of the ideal Chapman–Jouguet detonation. (The smaller value corresponds to the fuel-lean mixture.)

中文翻译：

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氢氧混合气在 100 毫米平面径向燃烧器中的连续爆轰，向周边排气

在内径为 100 mm 的平面径向燃烧室中，获得了氢氧混合物中连续自旋爆轰和连续多前爆轰的机制，并朝周边耗尽。根据混合物的特定流速确定爆震的贫燃料极限。对于连续自旋爆震，横向爆震波及其在燃烧器平面附近的流动被重建。由于沿燃烧器半径的速度的切向分量增加，爆震波明显弯曲。结果表明，尺度效应仅表现在旋转波的数量上。然而，它们的速度随着燃烧器尺寸的增加而增加。与理想的 Chapman-Jouguet 爆炸速度相比，连续爆炸的速度损失为 20-40%。（较小的值对应于贫油混合物。）