叶尖小翼对小流量跨声速压气机转子的影响研究

发布时间：2018-01-31 06:11

本文关键词： 叶尖小翼小流量压气机跨声速转子叶尖泄漏流叶尖泄漏涡　出处：《推进技术》2017年11期 　论文类型：期刊论文

【摘要】：为了控制压气机转子叶尖泄漏流动,减少叶尖泄漏流和叶尖泄漏涡对压气机内部流场带来的不利影响,针对小流量压气机进口跨声速转子进行了叶尖小翼的数值研究,探索了叶尖小翼对小流量跨声速压气机转子性能的影响和对叶尖泄漏流的控制机理。研究表明,4倍压力面宽度的压力面叶尖小翼可以使得压气机转子的流量裕度增加24.5%;吸力面叶尖小翼和压力面叶尖小翼影响失速的主要因素不同,吸力面叶尖小翼增大了吸力面侧流体的逆压梯度,扩大了低速流体区域,压力面叶尖小翼通过降低叶尖负荷,从而减弱泄漏强度,减小了低速流体区域。
[Abstract]:In order to control the tip leakage flow of the compressor rotor, the adverse effects of tip leakage flow and tip leakage vortex on the flow field in the compressor are reduced. A numerical study on the blade tip wing of the inlet transonic rotor of a small flow compressor is carried out. The influence of the blade tip wing on the rotor performance of the small flow transonic compressor and the control mechanism of the tip leakage flow are explored. The flow margin of the compressor rotor can be increased by 24.5m when the blade tip wing of the pressure surface is 4 times the width of the pressure surface. The main factors affecting the stall are different between the suction surface tip wing and the pressure surface tip wing. The suction surface tip wing increases the reverse pressure gradient of the suction side fluid and expands the low velocity fluid region. The tip wing of the pressure surface reduces the leakage intensity by reducing the tip load and reduces the low velocity fluid region.
【作者单位】：西北工业大学动力与能源学院;
【基金】：国家自然科学基金面上项目(51676162) 先进航空发动机协同创新中心资助
【分类号】：TH45
【正文快照】： 1引言压气机动叶和机匣间存在着叶尖间隙以防止相互接触,由于叶尖间隙的存在,在吸压力面压差以及动叶机匣相对运动的作用下,在叶尖间隙会产生由压力面向吸力面的泄漏流动(TLF),叶尖泄漏流在与主流掺混的过程中还会生成叶尖泄漏涡(TLV),造成流动损失和堵塞。Denton[1]的研究表

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