The paper presents a study for conditions for hydrogen self-ignition and flame spreading in a supersonic combustion chamber at the Mach number for the inlet flow equal to 4. The experimental model is a rectangular channel with a flame stabilizer performed as a backward-facing step. The fuel was injected before the step at the top and bottom walls through 8 round orifices which were oriented at angles 45° or 90°. Testing was performed for a wide range of flow parameters which were close to the flight conditions. The experiments performed allowed an efficient scheme of fuel injection for the processes of self-ignition and flame stabilization, which permits preventing choking the channel. It was found that the choice of the injection scheme and fuel injection pressure are critical for ignition conditions and allow controlling the combustion process.

本文提出了在进气流量等于4的马赫数下在超音速燃烧室中氢自燃和火焰蔓延的条件的研究。实验模型是矩形通道，带有火焰稳定剂作为向后步骤执行。在梯级之前，通过8个圆形的孔口将燃料喷射到顶壁和底壁，这些孔口的角度为45°或90°。针对接近飞行条件的各种流量参数进行了测试。进行的实验为自燃和火焰稳定过程提供了一种有效的燃料喷射方案，从而可以防止通道堵塞。已经发现，喷射方案和燃料喷射压力的选择对于点火条件是至关重要的，并且可以控制燃烧过程。