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为了探索高负荷压气机设计技术,提出了一种冲击-冲压式超声速压气机的设计方案。设计得到的冲击式转子在叶尖切线速度为457m/s下实现了4.6的压比和0.88的绝热效率,该转子的出口马赫数高达2.1,采用了冲压式静子来实现减速扩压,结合边界层吸气等手段,最终整级的压比为3.4,绝热效率为0.72。结果表明:这种超声速压气机设计方案可以实现较高的负荷和可以接受的效率,是一种值得关注与研究的高负荷压气机气动布局。
In order to explore the design technology of high-load compressor, a design scheme of impact-stamping supersonic compressor was proposed. The designed impact rotor achieves a pressure ratio of 4.6 and an adiabatic efficiency of 0.88 at a tip tangential speed of 457 m / s. The rotor has an outlet Mach number of up to 2.1. A ram-type stator is used to achieve deceleration and pressure expansion, Layer inhalation and other means, the final level pressure ratio of 3.4, adiabatic efficiency of 0.72. The results show that the design of this supersonic compressor can achieve high load and acceptable efficiency. It is a kind of aerodynamic layout of high load compressor that deserves our attention and research.