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根据某民用航空发动机大涵道比风扇1/2缩尺试验任务的需求,利用三维数值模拟软件对该风扇缩尺试验件各个转速下的内、外涵气动性能进行了数值仿真分析,并对缩尺几何、弹性恢复角及涵道比等参数对风扇缩尺试验件内、外涵气动性能的影响进行了对比分析.结果表明:该风扇缩尺试验件各转速下的内、外涵性能都基本达到设计指标;几何缩尺分别引起了风扇外涵、内涵设计点的效率分别降低了1.26%,0.77%;80%转速下,叶尖弹性恢复角减小0.36°使风扇外涵稳定工作裕度扩展了4.04%,但近设计点总压比和效率均有所衰减;双涵道风扇在不同涵道比状态下,内、外涵相互影响,流量-总压比及流量-绝热效率特性是在一定范围内的曲线带.
According to the requirements of a large bypass ratio fan 1/2 scale test mission of a civil aeroengine, the numerical simulation of the aerodynamic performance of the internal and external airfoils at various speeds was carried out by using three-dimensional numerical simulation software. Scale geometry, elastic recovery angle and the ratio of tunnel to the aerodynamic performance of the fan scale test were compared and analyzed.The results show that: the fan scale test under the speed of the internal and external performance All reached the design targets basically. The geometrical ruler caused the external condtions of the fans respectively, the efficiency of the connotation design points decreased by 1.26% and 0.77%, respectively. At 80%, the elastic recovery angle of the tip reduced by 0.36 °, The margin is extended by 4.04%, but the total pressure ratio and efficiency of the near design point are attenuated. In the condition of different bypass ratio, the inner and outer culverts interact with each other, and the flow-to-total pressure ratio and flow rate-adiabatic efficiency The characteristic is a curve band within a certain range.