高负荷过渡段的气动优化研究

对于具有内外双涵道某型涡扇发动机,其过渡段通道的损失主要来源于沿程损失和附面层分离损失,而影响附面层分离的主要是过渡段通道的扩张规律,落差越大,过渡段的负荷则越高。针对该问题,采用均匀设计的方法设计试验方案,通过CFD数值计算模拟方法对涡扇发动机风扇与压气机之间的过渡段流道进行了气动性能计算。该方法与结果为此类过渡段流道的设计优化提供了参考,并为以后的进一步改进和优化打下了坚实的基础。

Pneumatic Optimization Study of High Load Transition Section

For a turbofan engine with double culvert,the transition section channel loss mainly comes from the path loss and the loss of boundary layer separation,the influence of the boundary layer separation is mainly the expansion regulation of the transition section channel regulation,the greater the fall,the load of the transition section is higher.Using uniform design method to design test plan,aerodynamic performance calculation is carried out for the transition section which is between the extractor fan and compressor machine of a turbofan engine by adopting the method of CFD numerical simulation.The methods and results provide a reference for the design and optimization of the transition section and lay a solid foundation for further improvement and optimization for the future.