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为提高燃气涡轮发动机性能,将UCC技术应用在低压涡轮导向器上,建立低压涡轮导向叶片补燃室(Turbine Inter-vane Burners,TIB)模型。通过改变燃烧室结构,设计了3种涡轮叶间补燃室模型,利用计算流体力学软件FLUENT对燃烧室的流动及燃烧进行数值模拟,采用CFD的方法,分析燃烧室的燃烧和流动特性。结果表明:3种结构的涡轮叶间补燃室均提高了燃烧效率,选择的数学模型合理、计算方法可行,其结果可为涡轮叶间补燃室设计提供参考。
In order to improve the performance of gas turbine engine, UCC technology is applied to the low pressure turbine guide, and a Turbine Inter-vane Burners (TIB) model is established. By changing the structure of the combustion chamber, three models of afterburners for the turbine blades were designed. The flow and combustion in the combustion chamber were numerically simulated by the computational fluid dynamics software FLUENT. The combustion and flow characteristics of the combustion chamber were analyzed by CFD. The results show that all the three kinds of turbine intercover combustion chambers improve the combustion efficiency. The mathematical model is reasonable and the calculation method is feasible. The results can provide reference for the design of afterburner chamber between turbine blades.