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为了提高航空燃气涡轮发动机的推进效率和满足低排放的要求,提出了1种基于涡轮内补燃增推循环的超紧凑燃烧室──涡轮间燃烧室。建立了3种带不同轴向凹腔(AC)结构的TIB模型,比较了3种模型的流动性能和燃烧性能。计算结果表明:TIB的燃烧效率高达99.3%,AC结构的改变对燃烧效率影响较小,但对温度场分布影响较大。
In order to improve the propulsion efficiency of aviation gas turbine engines and meet the requirements of low emissions, an ultra-compact combustion chamber based on the recuperation and boost cycle in the turbine, an inter-turbine combustion chamber, is proposed. Three kinds of TIB models with different axial cavities (AC) structures were established, and the flowability and the combustion performance of the three models were compared. The calculation results show that the combustion efficiency of TIB is as high as 99.3%, the change of AC structure has little effect on the combustion efficiency, but has a great influence on the temperature field distribution.