ACTA AERONAUTICAET ASTRONAUTICA SINICA >
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
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.
CHEN Pingping , QIAO Weiyang , Karsten LIESNER , Robert MEYER . Boundary Layer Suction on Hub-corner Separation Loss in a Linear Compressor Cascade[J]. ACTA AERONAUTICAET ASTRONAUTICA SINICA, 2014 , 35(11) : 3000 -3011 . DOI: 10.7527/S1000-6893.2014.0015
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