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当增加动叶转角以进一步提升超、跨声速轴流压气机级负荷时,为解决其内部流动问题,提出了吸附式低反动度超、跨声速轴流压气机气动设计原理。分析了在该气动设计原理指导下,级内参数的演变规律与相互影响。利用该气动设计原理完成了一高负荷超声速轴流压气机气动设计,三维粘性数值模拟结果表明,在叶尖切线速度370m/s的前提下,实现了一级压比2.5,效率87%的压气机级设计。
When the rotor angle is increased to further enhance the transonic axial-flow compressor load, the aerodynamic design principle of the adsorption-trans-axial compressor is put forward to solve its internal flow problem. Under the guidance of the aerodynamic design principle, the evolution and interaction of parameters in the grade are analyzed. The aerodynamic design of a high-load supersonic axial-flow compressor is completed by using the aerodynamic design principle. The 3D viscous numerical simulation results show that the first-stage pressure ratio 2.5 and the 87% efficiency are achieved under the premise of a blade tip tangential speed of 370m / s Machine-level design.