| 摘要: |
| 随着飞机适航要求的提高，进口畸变对燃气轮机的影响也逐渐被重视起来。而飞行过程中燃气轮机所遇到的进口畸变经过动叶的传递后，往往会严重影响静叶进口气流角分布的均匀性，并恶化静叶的通流能力。为研究气流角畸变对静叶流场的影响，针对带有可调导叶的扇形叶栅，通过单独调整一片导叶角度而其它导叶角度不变的方式制造静叶进口畸变流场，并开展实验与仿真研究，分析该方法制造的畸变流场结构及其对静叶气动特性的影响。研究表明，采用的8号导叶旋转6°而其它导叶角度不变的方法可以改变静叶进口气流角、轴向速度、静压等参数的周向均匀度，实现静叶进口畸变流场。与均匀进口相比，气流角畸变度为3.22，气流角畸变度增加了1.14，并增加了静叶S8吸力面根部下通道涡的损失与影响范围，而对叶顶与中径处的影响相对较小。此外，受畸变流场影响的静叶流道总压恢复系数较均匀条件下略有下降。 |
| 关键词: 扇形叶栅 畸变 压气机 静叶 实验 数值模拟 |
| DOI：10.13675/j.cnki.tjjs.210012 |
| 分类号:V231.3 |
| 基金项目:国家自然科学基金（51576024）；中央高校基本科研业务费（3122019170）。 |
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| Effects of Distorted Flow Field on Aerodynamic Performance of Compressor Stator Vane Based on Sector Cascade |
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CHEN Tian-you1, SUN Peng2, FU Wen-guang2, HAN Ji-ang3
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1.College of Marine Engineering,Dalian Maritime University,Dalian 116026,China;2.College of Airworthiness,Civil Aviation University of China,Tianjin 300300,China;3.College of Naval Architecture and Ocean Engineering,Dalian Maritime University,Dalian 116026,China
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| Abstract: |
| With the improvement of airworthiness requirements， the effects of inlet distortion on gas turbines have been gradually taken into account. Moreover， the inlet distortion encountered by gas turbines during flight often seriously affects the uniformity of inlet flow angle distribution of stators and deteriorates the flow passage capacity of stators after passing through the rotors， Therefore， to study the effects of flow angle distortion on stator flow field， an experimental and simulation study was carried out on a fan cascade with adjustable guide vanes （AGV）. The inlet distortion was made by adjusting the angle of one guide vane separately while the other guide vanes are unchanged. The structure of the distorted flow field and its effect on the aerodynamic characteristics of the stator were analyzed. The results show that the circumferential uniformity of inlet flow angle， axial velocity， static pressure and other parameters can be changed by rotating 6° AGV8 while other guide vane angles remain unchanged， so as to produce inlet distortion. The flow angle distortion is 3.22， which increases by 1.14 compared with the uniform inlet condition. The distortion increases the loss and influence range of the passage vortex at the hub of S8 suction， but has little influence on the tip and middle span. In addition， the total pressure recovery coefficient at the flow path of the stators is lower than that under uniform condition. |
| Key words: Sector cascade Distortion Compressor Stator vane Experiment Numerical simulation |
