TY - JOUR
T1 - Corner separation dynamics in a high-speed compressor cascade based on detached-eddy simulation
AU - Li, Ruiyu
AU - Gao, Limin
AU - Ma, Chi
AU - Lin, Shiyan
AU - Zhao, Lei
N1 - Publisher Copyright:
© 2020 Elsevier Masson SAS
PY - 2020/4
Y1 - 2020/4
N2 - Corner separation is a vital unsteady flow phenomenon in a compressor and plays an essential role in flow field instability. Moreover, corner separation under high subsonic Mach number conditions is a scientific problem with practical engineering significance. The prime motivation of this work is using the most cost-effective method to more accurately resolve the corner separation phenomenon in a high-speed compressor cascade and to determine its inherent unsteady behavior under high-incidence conditions. Two configurations of the cascade are investigated, an incidence of 5.0° (stable) and 7.5° (unstable, near-stall), using a detached eddy simulation (DES) set to Re=7.5×105 and Ma=0.6 at the inlet boundary. The flow structures are analyzed after verifying the accuracy of the simulation. The dynamic mode decomposition (DMD) method is applied to analyze the main sources of instability in the flow field. By comparing the stable and unstable conditions, the suction surface separation vortex (SSV) found in the recirculation region is the key factor for flow instability. The mixture of the SSV and corner vortex (CV) is the main reason for the flow field becoming unstable and eventually causing a high-incidence stall. The formation and unsteady characteristics of the SSV at the near-stall condition are discussed. Suggestions for flow control and stall warning are also given. Thus, the results can provide a theoretical basis for the flow control of a high-speed compressor blade.
AB - Corner separation is a vital unsteady flow phenomenon in a compressor and plays an essential role in flow field instability. Moreover, corner separation under high subsonic Mach number conditions is a scientific problem with practical engineering significance. The prime motivation of this work is using the most cost-effective method to more accurately resolve the corner separation phenomenon in a high-speed compressor cascade and to determine its inherent unsteady behavior under high-incidence conditions. Two configurations of the cascade are investigated, an incidence of 5.0° (stable) and 7.5° (unstable, near-stall), using a detached eddy simulation (DES) set to Re=7.5×105 and Ma=0.6 at the inlet boundary. The flow structures are analyzed after verifying the accuracy of the simulation. The dynamic mode decomposition (DMD) method is applied to analyze the main sources of instability in the flow field. By comparing the stable and unstable conditions, the suction surface separation vortex (SSV) found in the recirculation region is the key factor for flow instability. The mixture of the SSV and corner vortex (CV) is the main reason for the flow field becoming unstable and eventually causing a high-incidence stall. The formation and unsteady characteristics of the SSV at the near-stall condition are discussed. Suggestions for flow control and stall warning are also given. Thus, the results can provide a theoretical basis for the flow control of a high-speed compressor blade.
UR - http://www.scopus.com/inward/record.url?scp=85078818596&partnerID=8YFLogxK
U2 - 10.1016/j.ast.2020.105730
DO - 10.1016/j.ast.2020.105730
M3 - 文献综述
AN - SCOPUS:85078818596
SN - 1270-9638
VL - 99
JO - Aerospace Science and Technology
JF - Aerospace Science and Technology
M1 - 105730
ER -