并联凹腔火焰稳定器超声速燃烧特性实验研究
发布时间：2019-03-22 14:53
【摘要】：为研究并联凹腔火焰稳定器的超声速燃烧特性,通过在凹腔上游喷注乙烯,采用单边扩张型燃烧室在当量比φ=0.43~1.07内进行了一系列直连式燃烧试验。模型燃烧室入口参数为Ma=3.46,总温Tt=1430K。基于燃烧室壁面静压分布、推力增益、燃料比冲和燃烧流场的可见光与纹影图像分析了并联凹腔在不同当量比下的火焰结构、流场特征和燃烧性能。结果表明,上、下壁面凹腔附近的流动条件差异显著,燃烧过程与当地流动条件之间的强烈耦合作用使得燃烧室内火焰分布显著不对称。发动机燃烧性能对当量比十分敏感,壁面静压水平和推力增益随当量比增加持续升高,但φ=0.43~0.62时的增加速率远大于φ=0.76~1.07时的。φ=0.43~0.62时,燃料比冲和燃烧效率随当量比增加而升高;而φ=0.76~1.07时,燃料比冲和燃烧效率随当量比增加而降低。
[Abstract]:In order to study the supersonic combustion characteristics of the parallel-cavity flame stabilizer, a series of direct-connected combustion experiments were carried out by injecting ethylene upstream of the cavity and using a single-side expandable combustion chamber in the equivalent ratio of 1 = 0.43 to 1.07. The inlet parameter of the model combustion chamber is Ma = 3.46, and the total temperature Tt = 1430K. The flame structure, flow field and combustion performance of the parallel cavity at different equivalent ratios are analyzed based on the static pressure distribution of the combustion chamber wall, the thrust gain, the fuel ratio and the combustion flow field. The results show that there is a significant difference in the flow conditions near the upper and lower wall cavities, and the strong coupling between the combustion process and the local flow conditions makes the flame distribution in the combustion chamber significantly asymmetric. The combustion performance of the engine is very sensitive to the equivalence ratio. The increase of the static pressure level and the thrust gain of the engine increases with the increase of the equivalent ratio, but the increase rate is much greater when the equivalence ratio is 0.43-0.62. When the ratio of fuel ratio and combustion efficiency increases with the increase of the equivalent ratio, the fuel ratio and the combustion efficiency decrease with the increase of the equivalent ratio when the ratio of the fuel ratio is between 0.43 and 0.62.
【作者单位】： 国防科技大学高超声速冲压发动机技术重点实验室;
【基金】：国家自然科学基金(91016028;11142010) 全国优秀博士学位论文作者专项资金(201257)
【分类号】：V231.2
[Abstract]:In order to study the supersonic combustion characteristics of the parallel-cavity flame stabilizer, a series of direct-connected combustion experiments were carried out by injecting ethylene upstream of the cavity and using a single-side expandable combustion chamber in the equivalent ratio of 1 = 0.43 to 1.07. The inlet parameter of the model combustion chamber is Ma = 3.46, and the total temperature Tt = 1430K. The flame structure, flow field and combustion performance of the parallel cavity at different equivalent ratios are analyzed based on the static pressure distribution of the combustion chamber wall, the thrust gain, the fuel ratio and the combustion flow field. The results show that there is a significant difference in the flow conditions near the upper and lower wall cavities, and the strong coupling between the combustion process and the local flow conditions makes the flame distribution in the combustion chamber significantly asymmetric. The combustion performance of the engine is very sensitive to the equivalence ratio. The increase of the static pressure level and the thrust gain of the engine increases with the increase of the equivalent ratio, but the increase rate is much greater when the equivalence ratio is 0.43-0.62. When the ratio of fuel ratio and combustion efficiency increases with the increase of the equivalent ratio, the fuel ratio and the combustion efficiency decrease with the increase of the equivalent ratio when the ratio of the fuel ratio is between 0.43 and 0.62.
【作者单位】： 国防科技大学高超声速冲压发动机技术重点实验室;
【基金】：国家自然科学基金(91016028;11142010) 全国优秀博士学位论文作者专项资金(201257)
【分类号】：V231.2
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