Blockage development in a transonic, axial compressor rotor
Blockage development in a transonic, axial compressor rotor
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DOI：
10.1115/1.2841741
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发表时间：
1998-07-01
影响因子：
1.7
通讯作者：
Suder, KL
中科院分区：
文献类型：
--
作者：
Suder, KL
详细的实验研究以理解和量化。跨音速轴流压缩机转子（NASA Rotor 37）流场中的堵塞问题已经得到解决。详细的激光风速计测量是在跨音速轴流压缩机转子的上游、内部和下游进行的。以设计速度的 100%、85%、80% 和 60% 运行，叶尖处的入口相对马赫数分别为 1.48、1.26、1.18 和 0.89。讨论了冲击油对堵塞发展的影响，涉及冲击/边界层相互作用和冲击/尖端间隙流动相互作用。结果表明，该转子端壁区域的堵塞是核心流动区域的2-3倍，当冲击强度足以分离吸力表面边界层时，核心流动区域的堵塞增加一倍以上。
A detailed experimental investigation to understand and quantify. the development of blockage in the flow field of a transonic, axial flow compressor rotor (NASA Rotor 37) has been undertaken. Detailed laser anemometer measurements were acquired upstream, within, and downstream of a transonic, axial compressor rotor. operating at 100, 85, 80, and 60 percent of design speed, which provided inlet relative Mach numbers at the blade tip of 1.48, 1.26, 1.18, and 0.89, respectively. The impact of the shock oil the blockage development, pertaining to both the shock/boundary layer interactions and the shock/tip clearance flow interactions, is discussed. The results indicate that for this rotor the blockage in the endwall region is 2-3 times that of the core flow region, and the blockage in the core flow region more than doubles when the shock strength is sufficient to separate the suction surface boundary layer.