A fluid-structure interaction model is developed to investigate the combustion and cooling performance of an aero-engine combustor. Cylindrical holes, conical holes, fan-shaped holes and console holes are introduced to reduce the thermal load of thermal barrier coatings (TBCs) in combustor, respectively. To reduce the coolant consumption, the number of film cooling holes in the first and second row at outer liner is decreased by 20% for comparison. The adoption of the four types holes leads to following results: the peak gas temperature increases from 2459.36 K to 2473.39 K, 2485.76 K, 2491.15 K, and 2464.57 K; the NO_x emission increases from 3.2306 g/kg to 3.4762 g/kg, 3.5197 g/kg, 3.5341 g/kg and 3.3494 g/kg; the peak working temperature of TBCs decreases by 149.01 K, 208.12 K, 248.64 K and 257.78 K respectively. Fan-shaped holes have the highest coolant discharge coefficient and correspond to the highest peak gas temperature and NO_x emission. The decrease of cooling hole number has very slight effect on TBCs peak working temperature, while it will reduce the peak gas temperature and the NO_x emission in the meanwhile. The cooling effectiveness of the console hole is the highest followed by the fan-shaped hole and the conical hole.

建立了流固耦合模型，以研究航空发动机燃烧室的燃烧和冷却性能。引入圆柱孔，圆锥孔，扇形孔和控制台孔以分别减少燃烧器中隔热涂层（TBC）的热负荷。为了减少冷却剂消耗，外衬的第一排和第二排中的薄膜冷却孔数量减少了20％，以作比较。四种类型的孔的采用导致以下结果：峰值气体温度从2459.36 K升高至2473.39 K，2485.76 K，2491.15 K和2464.57 K；该NO _X排放量从3.2306 g / kg增至3.4762 g / kg，3.5197 g / kg，3.5341 g / kg和3.3494 g / kg; TBC的峰值工作温度分别降低了149.01 K，208.12 K，248.64 K和257.78K。扇形孔具有最高的冷却剂排出系数和对应于最高峰气体温度和NO _X排放。冷却孔数的减少，对热障涂层高峰工作温度非常轻微的影响，而这将降低峰值气体温度和NO _X的同时发射。控制台孔的冷却效率最高，其次是扇形孔和锥形孔。