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亚音轴流压气机叶尖微喷气扩稳机理研究

Investigation of Stability Improvement Mechanism Based on Micro Tip Injection in Subsonic Axial Compressor
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摘要 叶尖喷气是提高压气机稳定工作裕度的一种重要方法。本文以某亚音轴流压气机孤立转子为研究对象,采用非定常数值模拟方法探索微喷气提高压气机稳定工作裕度的原因。数值模拟结果表明,高速喷气流降低了叶尖区域载荷,在inj2工况,导致流动条件恶化的叶尖二次涡没有出现,为此,压气机的稳定裕度得以提升。 Tip injection is known as an effective method to enhance the stability of the compressor. In order to clarify how the tip micro injection extends stall margin markedly, the unsteady numerical simulations were done on the subsonic axial flow isolated rotor. The numerical simulation results demonstrate that the high speed injection decreases the loading in the tip region and the tip secondary vortex disappears in the inj2 condition, consequently, the stall margin of the compressor is extended distinctly after injection.
出处 《航空科学技术》 2017年第4期1-7,共7页 Aeronautical Science & Technology
关键词 轴流压气机 数值模拟 叶尖二次涡 叶尖微喷气 axial compressor numerical simulation tip secondary vortex~ micro tip injection
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