针对航空发动机进气温度畸变评定试验需求，采用数值计算方法对某型航空发动机温度畸变氢燃气发生器开展研究。分析了氢燃气发生器在不同扇区供氢和不同当量比供氢条件下的火焰传播特性及热扩散规律。结果表明:长、短燃烧器支杆间隔排布的氢燃气发生器构型能最优化管道内的燃烧分布，且氢燃气发生器的燃烧和热扩散规律由火焰传播特性决定。部分扇区供入燃料时，高温区主要分布在相对应的扇区附近，且当量比为0.1时，高温区向外扩散角度一定，约为20°；供氢扇区角度增大，对应扇区出口温度不均匀度增大，但整环出口温度不均匀度在180°扇区喷氢时最大。随着当量比增大，高温燃气扩散范围增大，发生温度畸变的范围增大了1.5倍，同时出口温度不均匀度和空间压力畸变也逐渐增大。

In response to the experimental requirements for the assessment of intake air temperature distortion in aviation engines, a numerical computation method was employed to investigate a specific type of hydrogen burner used in aviation engines with temperature distortion. The study analyzed the flame propagation characteristics and thermal diffusion patterns of the combustor under different hydrogen supply conditions in various sectors and at different equivalence ratios. The results indicate that a configuration with long and short burner bars arranged alternately optimizes the combustion distribution within the duct. Moreover, the combustion and heat diffusion patterns of the hydrogen burner are determined by the characteristics of flame propagation. When fuel is supplied to specific sectors, high-temperature zones are primarily localized near the corresponding sectors, and at a equivalence ratio of 0.1, the high-temperature zone diffuses outward at a fixed angle, approximately 20°. As the sector angle for hydrogen supply increases, the corresponding sector temperature non-uniformity at the outlet also increases, but the overall temperature non-uniformity at the outlet is greatest when hydrogen is sprayed in a 180° sector. With an increase in the equivalence ratio, the range of high-temperature gas diffusion increases, and the area affected by temperature distortion expands by a factor of 1.5. Concurrently, the temperature non-uniformity at the outlet and the spatial pressure distortion also gradually increase.

高超声速气膜冷却的热结构耦合特性及强度评定方法研究项目