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为了揭示叶顶喷气对压气机稳定裕度的影响规律,对一跨声速轴流压气机进行三维非定常数值模拟,结合试验设计与统计学分析的方法对叶顶喷气展开参数化研究,并分析了叶顶喷气的扩稳机理。研究表明,叶顶喷气整体上提升了压气机的性能,通过激励叶顶环壁附面层抑制叶顶泄漏涡堵塞,达到提升压气机稳定裕度的目的。同时,叶顶喷气会引起压气机失速类型的变化。不同喷气量下的喷气规律是不同的,喷气量与喉部高度、喷气角度间存在交互作用。喷气量较小时应减小喷嘴喉部高度,在相对坐标系下沿转子叶顶前缘中弧线方向喷气;喷气量较大时应增加喉部高度,避免引起叶顶过载失速,喷气应提供正预旋来减小叶顶攻角。喷嘴应与转子叶顶前缘保持一定距离。
In order to reveal the influence law of tip jet on the stability margin of compressor, a three-dimensional unsteady numerical simulation of a transonic axial-flow compressor was carried out. The parametric study on the tip-jet was carried out with experimental design and statistical analysis The blade tip of the expansion mechanism. The research shows that the tip-jet enhances the performance of the compressor as a whole and suppresses the blockage of the tip leakage vortex by encouraging the top wall of the top ring wall to enhance the stability margin of the compressor. At the same time, tip-jet can cause changes in the type of compressor stall. The jet law is different under different jet amount, there is an interaction between jet amount and throat height, jet angle. When the amount of gas is small, the nozzle throat height should be reduced, and the gas should be jetted in the arc direction along the leading edge of the rotor blade in the relative coordinate system. If the amount of gas is larger, the throat height should be increased to avoid causing the top of the blade to stall and the jet should provide Pre-spin to reduce the blade angle of attack. The nozzle should be at a distance from the leading edge of the rotor tip.