ACTA AERONAUTICAET ASTRONAUTICA SINICA >
Prestall process in low-speed axial compressor with single circumferential casing groove
Received date: 2015-01-12
Revised date: 2015-05-13
Online published: 2015-05-25
Supported by
National Natural Science Foundation of China (51106153, 51176188)
In order to further understand the impact of circumferential casing groove axial location on stall mechanism of compressor, a tip sensitive low-speed single rotor is tested and numerically simulated. The results show that the location with the maximum stall margin improvement (SMI) is near the mid-chord of blade tip and the location with the minimal SMI is around 20%-30% axial tip chord aft of blade leading edge. Numerical results are acquired from an unsteady multi-passage numerical scheme. For smooth casing and the optimal groove, the interface between the tip leakage flow and main flow reaches blade leading edge under the near stall condition and spike stall inception appears; but for the worst groove, the interface is away from blade leading edge under the near stall condition, around 20% axial tip chord aft of blade leading edge, and a conversion between quasi-modal stall inception and spike stall inception is captured.
GAO Lipeng , DU Juan , LI Jichao , LIN Feng , NIE Chaoqun . Prestall process in low-speed axial compressor with single circumferential casing groove[J]. ACTA AERONAUTICAET ASTRONAUTICA SINICA, 2015 , 36(12) : 3822 -3831 . DOI: 10.7527/S1000-6893.2015.0136
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