内机匣故障对燃烧室性能影响的数值与试验研究  

Numerical and Experimental Study of Effect of Inner Casing Failure on Combustor Performance

作　　者：王文波[1] 岳明[1] 金捷[1] 

机构地区：[1]北京航空航天大学能源与动力工程学院,北京100191

出　　处：《航空发动机》2016年第2期83-87,共5页Aeroengine

摘　　要：为了研究内机匣故障对燃烧室性能的影响,在对某回流燃烧室的正常件及小弯管有裂缝故障件进行试验的基础上,通过可实现的k-ε湍流模型、颗粒随机轨道模型、火焰面模型和Kundu化学反应机理对模型燃烧室内3维2相燃烧流场进行了数值模拟,分别对小弯管不同裂缝长度(占模型弧长的10%、20%、30%、40%、50%)且最宽处为0.55 mm不变情况下的模型燃烧室的出口温度分布进行对比分析。结果表明:裂缝漏气导致叶尖温度降低,叶根温度升高,不利于涡轮转子叶片工作。In order to study the effect of inner casing failure on combustor performance, three dimensional two-phase combustion flow fields in a model combustor were simulated using realizable k-ε turbulent model,particles stochastic trajectory model, flame let models and Kundu chemical reaction mechanism based on the experiment of a reverse-flow combustor and the one with cracks in the small bend. The outlet temperature distribution of the model combustor in the situation of different crack length（accounting for 10%,20%,30%,40%,50%of the arc length of the model） and the widest position＇s dimension which was a fixed value of 0.55 mm were compared and analyzed. The result shows that the crack leakage lead to the temperature dropping at blade tip but rising at the blade root, which is not conducive to the turbine rotor blade.

关 键 词：内机匣 故障 试验 数值模拟 出口温度分布 航空发动机 

分 类 号：V231.2[航空宇航科学与技术—航空宇航推进理论与工程]