为了提升航空发动机推重比,设计了一种耦合压气机出口导向器和涡轮进口导向器的一体化倾斜燃烧室方案,基于数值仿真方法对倾斜燃烧室与传统燃烧室分别开展数值仿真分析,计算结果表明：与传统燃烧室相比,本文设计的倾斜燃烧室能够保证在总压损失和燃烧效率基本不变、出口温度分布合理的情况下,将燃烧室火焰筒长度缩短29.26%；相比传统燃烧室,倾斜燃烧室内回流区周向宽度降低,回流量减少,同时,倾斜燃烧室出口温度分布虽然合理,但温度分布均匀性下降；在倾斜燃烧室出口截面,气流在周向上出现偏转以冲击涡轮工作叶片,气流偏转角呈现上下两端高,中间低的特点,并且与冷态结果相比,燃烧态下气流偏转角更小,在冷态时,出口气流发生33°～68°偏转,在燃烧态,出口气流发生21°～38°偏转。

In order to improve the thrust-weight ratio of aero-engine, an integrated inclined combustion chamber scheme coupling compressor outlet guide and turbine inlet guide is designed. Based on the numerical simulation method, the numerical simulation analysis of the inclined combustion chamber and the conventional combustion chamber is carried out respectively. The calculation results show that compared with the conventional combustion chamber, the inclined combustion chamber designed in this paper can shorten the length of the combustion chamber flame tube by 29.26 % under the condition that the total pressure loss and combustion efficiency are basically unchanged and the outlet temperature distribution is reasonable. Compared with the conventional combustion chamber, the circumferential width of the recirculation zone in the inclined combustion chamber is reduced, and the return flow is reduced. At the same time, although the outlet temperature distribution of the inclined combustion chamber is reasonable, the uniformity of the temperature distribution decreases. At the outlet section of the inclined combustion chamber, the airflow deflects in the circumferential direction to impact the turbine working blade. The airflow deflection angle is high at both ends and low in the middle. Compared with the cold state results, the airflow deflection angle is smaller in the combustion state. In the cold state, the outlet airflow deflects 33 ° ~ 68 °.In the combustion state, the outlet airflow deflects 21 ° ~ 38 °.

V231.2

南京航空航天大学前瞻布局科研专项资金