边界层吸气对压气机叶栅角区分离损失的控制
收稿日期: 2013-11-25
修回日期: 2014-03-06
网络出版日期: 2014-04-08
Boundary Layer Suction on Hub-corner Separation Loss in a Linear Compressor Cascade
Received date: 2013-11-25
Revised date: 2014-03-06
Online published: 2014-04-08
压气机角区的大范围回流通常会引起叶片通道中的三维阻塞现象,并伴随有强烈的掺混流动损失.采用德国航空航天中心(DLR)开发的TRACE程序,在其推进技术研究所的高速压气机叶栅试验台(包含5个NACA65 K48直叶片)上,研究了位于端壁上的边界层吸气措施——叶片弦中近尾缘吸气槽(MTE)对该直压气机叶栅通道的角区分离进行控制,减小二次流动损失,进而削弱其对总损失的影响.通过基于定常雷诺平均Navier-Stokes(RANS)方法的数值模拟研究与相应的试验研究对比,端壁边界层吸气能够较好地重新组织角区气流流动,减弱附着于叶片吸力面尾缘的集中脱落涡,使得角区分离涡强度显著降低,由此引起的二次流损失也明显降低,与无吸气状态相比最大降幅可达81.2%;在设计状态下采用吸气流量率为1%的MTE,总压损失有很大程度的降低:在数值计算中,降幅为15.2%;试验测量中为9.7%.
关键词： 压气机角区分离; 端壁边界层吸气; 叶片弦中近尾缘吸气槽; 高速压气机叶栅试验台; 总压损失
陈萍萍 , 乔渭阳 , Karsten LIESNER , Robert MEYER . 边界层吸气对压气机叶栅角区分离损失的控制[J]. 航空学报, 2014 , 35(11) : 3000 -3011 . DOI: 10.7527/S1000-6893.2014.0015
The large reverse flow in the compressor hub-corner region usually leads to three-dimensional blockage in the blade passage, accompanied by a strong mixing flow loss. With TRACE code (developed by German Aerospace Center (DLR)), the endwall boundary layer suction with MTE (Middle suction slot near the Trailing Edge) is applied numerically to a high-speed compressor linear cascade test rig consisting of five NACA65 K48 profiles in the DLR Institute of Propulsion Technology to dismiss the effect of corner separation, to decrease the secondary flow and thus to reduce its influence on the total pressure loss. The detailed flow phenomena are revealed by the steady Reynolds-averaged Navier-Stokes (RANS) investigations with experimental validation at the design operating condition. The results show that MTE at the endwall close to the suction surface can effectively reorganize the corner flow, reduce the concentrated shed vortex attached to the trailing edge of the blade suction surface and thus decrease the corner vortex intensity significantly. Consequently, the related secondary flow loss is reduced essentially, the maximum being up to 81.2% compared to the no suction case. Under the design operating condition, by using of MTE suction slot, the total pressure loss is obviously decreased by about 15.2% in CFD calculation and 9.7% in the test.
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