摘要
由于当代新的歼击机发展的需要 ,推重比 1 0以上的涡扇发动机的研制势在必行 ,而对于涡轮部件 ,采用超跨音、大负荷、低稠度、无导叶、大转折角的对转涡轮方案是一个重大的技术措施。它将大幅度减轻发动机重量 ,提高推动比。文中对此论述了它的主要优点 ,以及由此带来涡轮气动设计、计算方面的新问题和新概念。我们设计并制造出了试验件 ,并与 6 0 8所合作在北航建立了对转涡轮试验台。
To meet the needs for developing contemporary new generation fighters, it is imperative to develop fan turbo-engine with thrust loading ratio of exceeding ten. Adopting contra-rotating turbine which is characterized by transonic-supersonic profiles, large load, low blade density, no guide vanes and high deflection angle is an important measure. It would greatly reduce the weight of engine and raise the thrust loading ratio. This paper reviews its primary advantages and new requirements for aerodynamics design and computing. A contra-rotating turbine test rig has been constructed in Beijing University of Aeronautics and Astronautics with cooperation of 608 Research Institute of China Aviation Industry.
出处
《航空动力学报》
EI
CAS
CSCD
北大核心
2002年第4期495-499,共5页
Journal of Aerospace Power
