为探究不同构型对射流稳焰燃烧室冷态流动特性的影响,文中在原有燃烧室构型的基础上提出了3种不同组合构型的射流稳焰燃烧室。首先对燃烧室模型进行网格无关性验证,确定最终数值模拟的网格数量,在此基础上对4种构型射流稳焰燃烧室进行冷态模拟研究,从速度流线、涡结构、湍动能分布、气相掺混度以及丙烷质量分数5个方面来分析模拟结果。研究结果表明:除构型3外,其余3种构型均能形成3对旋涡,分别位于燃料喷口处、空气射流孔的左侧以及燃烧室下游,其中构型2的旋涡结构较为独立,边界比较清晰。燃烧室主燃区(0~0.06 m)内,构型2的湍动能最大,丙烷质量分数最小,气相掺混度最高,表明该几何模型更有利于燃料与空气的掺混。燃烧室下游(0.06~0.40 m),4种构型的丙烷质量分数均比主燃区内低。

In order to explore the cold flow characteristics of different configurations of jet-stabilized combustor, three combustor geometries are proposed on the basis of original geometry. First, the grid independence of the combustors is verified to determine the grid number for the final numerical simulation. On this basis, the cold simulations of four combustor geometries are carried out. The numerical results are analyzed from five aspects:velocity streamline, vortex structure, turbulent kinetic energy distribution, gas mixing degrees and propane mass fraction. The results show that except geometry 3, the other three combustor geometries could be form three pairs of vortices, which were separately located at the fuel jet hole, the left side of the air jet hole and the combustor downstream. The vortex structure of combustor geometry 2 was relatively independent and the boundary was relatively clear. In the combustor primary zone (0~0.06 m), the turbulent kinetic energy of geometry 2 was the largest, the mass fraction of propane was the smallest, and the gas mixing degrees was the highest, indicating that the geometric model was beneficial for the mixing of fuel and air. Downstream of the combustor (0.06~0.40 m), the mass fraction of propane in the four configurations was lower than that in the combustor primary zone.